A lubricating oil and mist separation system for an aeroengine

Abstract

This invention relates to the field of oil mist separation technology for aero-engines, and more particularly to an oil and mist separation system for aero-engines, comprising a condition detection component, a controller, and a condition adjustment component. The condition detection component includes a pressure sensor located at the oil and gas inlet of the separation system for real-time acquisition of the oil and gas inlet pressure parameters of the separation system. Through the linkage of the pressure sensor, temperature sensor, and controller, the system can actively adapt to the full range of operating conditions of the aero-engine, from idle speed to high thrust and high flow rate. At the same time, the introduction of an annular heating component enables the system to have thermal self-compensation capability in extreme low-temperature environments. By utilizing an active adjustment mechanism based on real-time feedback, the system overcomes the shortcomings of traditional fixed structures in handling diverse operating conditions, effectively improving the comprehensive adaptability of the oil mist separation system to complex aero-engine operating environments and conditions.

Description

Technical Field

[0001] This invention relates to the field of oil mist separation technology for aircraft engines, and more particularly to an oil and mist separation system for aircraft engines. Background Technology

[0002] Due to their operational characteristics, aircraft turbojet engines require the compressor impeller rotor and turbine rotor to work together. The rotation of the shaft between the rotors relies on bearings for support. To reduce bearing friction, lubrication with lubricating oil is necessary. When the engine is running, the engine body temperature, combined with the heat generated by the friction of the ball bearings, causes the lubricating oil to evaporate to a certain extent. In the pipeline, the lubricating oil and gas are mixed together. After the engine has been running for a long time, the amount of lubricating oil gas evaporated in the lubricating oil circulation pipeline gradually increases, which is detrimental to the operation of the lubricating oil system. This can lead to the bearings not being fully lubricated, resulting in bearing wear and affecting the engine's service life.

[0003] Existing oil mist separators mostly rely on passive drive via the coaxial connection of the engine main shaft and gearbox, with their rotational speed completely following the engine's operating conditions. At low speeds, they suffer from insufficient centrifugal separation of oil mist, lack independent adjustment capabilities, and while integrated within the engine, their compact structure makes disassembly and assembly difficult, hindering rapid replacement and making them unsuitable for rapid maintenance in field operations. Independent separators, on the other hand, are too bulky to meet the needs of small engines requiring increased thrust-to-weight ratio and weight reduction.

[0004] Furthermore, for small aircraft engines, due to their small size, the lubricating oil tank is initially filled with lubricating oil. During lubrication, the oil comes into contact with air, generating a certain amount of mist. When this mist returns to the lubricating oil tank, it occupies space, reducing the effective amount of lubricating oil and affecting lubrication. Therefore, it is necessary to effectively separate the oil-air mixture in the lubricating oil circulation pipeline, expelling the gas and ensuring that the lubricating oil circulation within the engine remains in a liquid state, thereby preventing oil supply interruption or damage to the oil film.

[0005] Existing oil mist separators mainly have the following defects: Firstly, most existing oil mist separators rely on passive drive via the coaxial connection of the engine spindle and gearbox, with their rotational speed completely following engine operating conditions. Under low-speed conditions such as engine start-up, idling, or slow speed, the centrifugal force field weakens effectively as the speed decreases, resulting in insufficient centrifugal separation of oil mist and difficulty in guaranteeing separation efficiency; such passively driven structures lack independent adjustment capabilities. Secondly, existing passively driven separators are mostly integrated inside the engine. Although the overall structure is compact, it is difficult to disassemble and assemble, and cannot be quickly replaced, which is not suitable for the needs of rapid maintenance in the field. Third, the existing independent separators are too large and cannot meet the needs of small engines to increase thrust-to-weight ratio and achieve weight reduction. Fourth, the structural parameters of existing separators, such as the spacing between the separation discs and the temperature of the separation chamber, are fixed after manufacturing and cannot be adaptively adjusted according to changes in intake pressure, intake flow rate, and external ambient temperature under different engine operating conditions. Under high-pressure and high-flow conditions, the oil-gas flow channel with a fixed gap is easily broken by the high-pressure airflow, causing the oil film ejected by centrifugation to be re-entrained. Under low-speed and low-flow conditions, the fixed gap makes it difficult to further improve the collection efficiency of tiny oil droplets. In high-altitude and low-temperature environments, the fixed structure may also lead to a decrease in separation efficiency or even unstable operation due to increased lubricating oil viscosity and local icing. Summary of the Invention

[0006] Therefore, the present invention provides an oil and mist separation system for aero engines to overcome the problem that existing technologies cannot operate stably in a wide temperature range and under different intake conditions; This application maintains a constant high-speed centrifugal force field through independent motor drive, and combines it with a closed-loop adaptive adjustment mechanism consisting of working condition detection components, controller and working condition adjustment components to achieve efficient separation of oil droplets and gas, reduce the gas content in the lubricating oil tank, and enable the separation system to operate stably in a wide temperature range and under different intake conditions while maintaining the preset separation efficiency. The overall structure is lightweight and easy to disassemble and replace quickly.

[0007] To achieve the above objectives, the present invention provides an oil and mist separation system for an aircraft engine, comprising: The separator base assembly and the separator end cap connected to the separator base assembly; the separator shaft arranged axially within the separator base assembly; the motor assembly for driving the separator shaft to rotate; the first separator disc and the second separator disc arranged parallel to each other on the separator shaft, wherein the outer diameter of the first separator disc is larger than the outer diameter of the second separator disc; and further comprising a working condition detection assembly, a controller and a working condition adjustment assembly.

[0008] The operating condition detection component is used to acquire the external ambient temperature parameters and / or internal oil and gas intake pressure parameters of the separation system in real time; the operating condition adjustment component is located on the separator base assembly or the separator shaft, and the controller is used to control the operating condition adjustment component to perform internal structural modification actions according to the parameters fed back by the operating condition detection component; wherein, the internal structural modification actions include adjusting the axial clearance between the first separation disk and the second separation disk and / or adjusting the local temperature in the separation chamber, so as to achieve stable operation of the separation system under a predetermined low temperature environment and maintain a preset separation efficiency under different intake conditions.

[0009] Furthermore, the operating condition detection component includes a pressure sensor disposed at the oil-gas inlet of the separation system; the operating condition adjustment component is connected to the side of the first separation disc or the second separation disc, and is used to push and pull the corresponding separation disc along the axial direction to change the axial clearance; the controller is configured to: when the oil-gas inlet pressure detected by the pressure sensor is higher than a preset high-pressure threshold, control the operating condition adjustment component to increase the axial clearance; when the oil-gas inlet pressure detected by the pressure sensor is lower than a preset low-pressure threshold, control the operating condition adjustment component to decrease the axial clearance.

[0010] Furthermore, the separator base assembly is provided with a hydraulic oil passage that connects to the lubricating oil pump of the aircraft engine, and the operating condition adjustment assembly includes a hydraulic drive sleeve or a hydraulic drive spring disposed around the first or second separator plate; the lubricating oil pressure entering the hydraulic oil passage drives the hydraulic drive sleeve or the hydraulic drive spring to move axially to change the axial clearance.

[0011] Furthermore, the operating condition adjustment component includes an electromagnetic actuation component connected to the side of the first or second separation disc, the electromagnetic actuation component pushing and pulling the corresponding separation disc axially according to the instructions of the controller.

[0012] Furthermore, the operating condition detection component includes a temperature sensor disposed within the separator base assembly, and the operating condition adjustment component includes an annular heating component disposed within the separator end cover or the wall of the separation chamber; when the external ambient temperature detected by the temperature sensor is lower than a preset low temperature threshold, the controller controls the annular heating component to start heating.

[0013] Furthermore, the motor assembly is an external rotor motor, including a motor stator and a motor rotor. The motor stator is fixed inside the separator base assembly, and the motor rotor is fixed on the inner wall of the separator rotor housing and rotates synchronously with the separator shaft. The controller controls the motor assembly to operate at a preset constant speed so that the separation system has a constant centrifugal force field under any operating condition of the aero-engine.

[0014] The beneficial effects of this invention are that, through the linkage of pressure sensors, temperature sensors and controllers, the system can actively adapt to the full range of operating conditions of the aero-engine, from idle speed to high thrust and high flow rate; at the same time, the introduction of the annular heating component enables the system to have thermal self-compensation capability in extreme low temperature environments, and by using an active adjustment mechanism based on real-time feedback, it makes up for the shortcomings of traditional fixed structures that cannot take into account multiple changing operating conditions, effectively improving the comprehensive adaptability of the oil mist separation system to complex aero-operating environments and conditions.

[0015] This invention provides a variety of flexible gap adjustment methods, such as electromagnetic actuation and lubricating hydraulic drive. It can use precise electronic control feedback or utilize the engine's own lubricating oil pressure to achieve delay-free follow-up adjustment. Combined with the constant centrifugal force field maintained by the independent drive of the external rotor motor, it can provide highly compatible adaptation solutions for different types of aero engines in terms of electrification level, hydraulic system characteristics and spatial layout, which greatly enhances the overall adaptability and versatility of the oil mist separation system to different engine platforms.

[0016] The system actively increases the clearance to expand the oil-gas passage under high flow and high pressure conditions, effectively preventing the high-pressure airflow from breaking through the centrifugal oil film. Under low flow and idling conditions, it actively reduces the clearance to shorten the radial distance between the separation disk and the airflow, efficiently capturing tiny oil droplets. It also implements a bidirectional adaptive adjustment strategy for extreme flow values, ensuring that the system is always at the optimal separation operating point under different aerodynamic loads, effectively improving the system's wide-range adaptability to the drastic fluctuations in aero-engine flow.

[0017] The system achieves efficient coarse and fine separation through first and second separation discs with distinct outer diameter gradients. Combined with the safety redundancy design of the pressure balance bypass regulating valve and the built-in lubricating oil return channel, the system achieves compactness and lightweight design while ensuring operational safety under extreme conditions. By utilizing an integrated architecture that combines efficient centrifugal separation, active regulation, and passive safety protection, the system effectively enhances its comprehensive adaptability to the stringent boundary constraints of aero-engines.

[0018] The present invention has the following advantages over the prior art: (1) The present invention utilizes a motor assembly to independently drive the separator shaft, so that it maintains a preset constant high speed (e.g., 20,000 rpm) to operate, thereby providing a constant and sufficient centrifugal force field under any working conditions such as engine start, idling, slow speed, and cruising. This overcomes the defects of existing passive coaxial drive separators, such as insufficient centrifugal separation under low speed conditions and separation efficiency fluctuating with engine speed, so that the maximum separation efficiency can always remain stable.

[0019] (2) This invention forms a closed-loop adaptive adjustment mechanism through the working condition detection component, controller, and working condition adjustment component. It can actively adjust the axial clearance between the first and second separation discs and / or the local temperature in the separation chamber according to the real-time oil and gas intake pressure and / or the external ambient temperature. Under high pressure and high flow conditions, the axial clearance is increased and the oil and gas flow channel is expanded to prevent the high pressure airflow from breaking through the oil film ejected by centrifugation. Under low speed and low flow conditions, the axial clearance is reduced and the distance between the edge of the separation disc and the core area of ​​the airflow is shortened to improve the collection efficiency of tiny oil droplets. Heating is started in low temperature environment to avoid excessively high lubricating oil viscosity or local freezing, which would lead to unstable operation. As a result, the separation system can maintain the preset separation efficiency and operate stably in a wide temperature range and under different intake conditions.

[0020] (3) The present invention has a wide temperature adaptability and can work in the range of 55℃~150℃, especially suitable for the use requirements of low temperature environment at an altitude of 15km.

[0021] (4) The present invention has a lightweight overall structure and a small size (e.g., about 70 mm in length and about 38 mm in width). It adopts an independent modular layout, which is convenient for quick disassembly and replacement, adapts to the needs of rapid maintenance in the field, and meets the lightweight requirements of improving the thrust-to-weight ratio of small engines. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the lubricating oil and mist separation system for the aero-engine of the present invention. Figure 2 This is a cross-sectional view of the lubricating oil and mist separation system according to an embodiment of the present invention; Figure 3 This is a schematic diagram illustrating the separation principle of an embodiment of the present invention. Detailed Implementation

[0023] To make the objectives and advantages of the present invention clearer, the present invention will be further described below with reference to embodiments; it should be understood that the specific embodiments described herein are merely for explaining the present invention and are not intended to limit the present invention.

[0024] Preferred embodiments of the present invention will now be described with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are merely illustrative of the technical principles of the present invention and are not intended to limit the scope of protection of the present invention.

[0025] It should be noted that in the description of this invention, the terms "upper", "lower", "left", "right", "inner", "outer", etc., which indicate directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. This is only for the convenience of description and is not intended to indicate or imply that the device or element must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this invention.

[0026] Furthermore, it should be noted that, in the description of this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0027] Please see Figure 1As shown, it is a structural schematic diagram of the lubricating oil and mist separation system of the aero-engine of the present invention, which includes: a separator base assembly, a separator end cover, a separator shaft, a motor assembly, a first separation disc, a second separation disc, and an adaptive adjustment subsystem including a condition detection component, a controller, and a condition adjustment component.

[0028] The separator base assembly is fixedly connected to the separator end cover, forming the outer shell of the separation system. The separator shaft is axially positioned within the shell and is supported by two bearings installed in the separator base assembly and separator end cover, ensuring coaxiality and operational stability of the shaft during high-speed rotation. The motor assembly preferably uses an external rotor motor, including a motor stator and a motor rotor.

[0029] The motor stator is fixed inside the separator base assembly, and the motor rotor is fixed on the inner wall of the separator rotor housing assembly.

[0030] The head of rotor housing assembly 1 is locked to the separator shaft by slotted conical set screws.

[0031] When the motor is working, the motor rotor drives the rotor housing assembly 1 and the separator shaft to rotate synchronously at high speed, thereby generating a strong centrifugal force field in the separation chamber.

[0032] Please see Figure 2 As shown, it is a cross-sectional view of the lubricating oil and mist separation system according to an embodiment of the present invention. In the figure: The first and second separation discs are mounted parallel to each other along the axial direction on the separator shaft and rotate synchronously with the shaft.

[0033] Along the direction of oil and gas flow, the oil and gas mixture first reaches the first separation plate, and then the second separation plate.

[0034] The outer diameter of the first separation disk is designed to be larger than that of the second separation disk.

[0035] The basic working principle of this separation system is as follows: Figure 3 As shown, it is a schematic diagram of the separation principle of an embodiment of the present invention. In the figure: The oil-gas mixture from the lubricating oil tank or bearing cavity of the aircraft engine enters the separation system tangentially through the oil-gas inlet located on the separator base assembly.

[0036] The oil-gas mixture first enters the hollow channel inside the separator shaft, where it lubricates the internal bearings during the initial flow phase. Subsequently, the mixture flows through the high-speed rotating first separation disc.

[0037] Under strong centrifugal force, denser lubricating oil droplets are thrown towards the outer wall of the separation chamber, collect, flow out through the lubricating oil outlet, and are recycled back to the lubricating oil tank. Denser gas, on the other hand, gathers towards the center of the rotating shaft.

[0038] Some tiny oil droplets that were not completely separated at the first separation plate continued to flow downstream with the gas to the second separation plate. As the second separation plate also rotated at high speed, the remaining oil droplets were thrown against the outer wall for separation a second time.

[0039] After being separated in two stages, the purified gas rises along the central channel of the rotating shaft under the impetus of the subsequent airflow, and is finally discharged from the exhaust port to the atmosphere or the engine intake.

[0040] Because the first separating disc has a larger diameter and a higher edge velocity, it undertakes the main centrifugal separation task; the second separating disc plays the role of fine separation and preventing oil back mixing.

[0041] To overcome the problem of low separation efficiency of traditional passively driven separators under low engine speed conditions, the controller in this invention is configured to control the motor assembly to always operate at a preset constant high speed (e.g., 20,000 rpm).

[0042] This means that regardless of whether the aircraft engine is starting, idling, slow, cruising, or operating at maximum thrust, the separator shaft maintains a constant high-speed rotation, thereby maintaining a constant and sufficient centrifugal force field within the separation chamber, ensuring that the oil mist separation efficiency is always at its best under any engine operating condition.

[0043] This separation system is designed to operate normally within a wide temperature range of 55℃ to 150℃, and is especially suitable for low-temperature environments at an altitude of 15km.

[0044] Under high-temperature conditions, the materials and fit tolerances of all system components are designed to withstand 150℃. In low-temperature environments, the heat generated by the high-speed rotating motor and the heat carried by the lubricating oil itself (typically around 80-90℃) help maintain the internal temperature of the system.

[0045] As a further low-temperature protection measure, in this embodiment, the operating condition detection component includes a temperature sensor (not shown in the figure) installed in the separator base assembly, and the operating condition adjustment component includes an annular heating component (not shown in the figure) embedded in the separator end cap or attached to the wall of the separation chamber.

[0046] The temperature sensor monitors the ambient temperature of the separation system in real time and feeds the signal back to the controller. When the ambient temperature is detected to be lower than a preset low temperature threshold (e.g., 40°C), the controller instructs the annular heating assembly to start heating and increase the local temperature inside the separation chamber.

[0047] This active heating measure effectively avoids problems such as increased flow resistance and separation difficulties caused by excessively high oil viscosity at low temperatures, or the impact of icing on the inner wall of the cavity on rotor operation stability. It ensures that the system can still operate reliably in extreme low temperature environments, and when the temperature rises above the threshold, the controller controls the heating components to stop working to save energy.

[0048] The separator base assembly and the separator end cover connected to the separator base assembly; the separator shaft arranged axially within the separator base assembly; the motor assembly for driving the separator shaft to rotate; the first and second separator discs arranged parallel to each other on the separator shaft, the outer diameter of the first separator disc being larger than the outer diameter of the second separator disc; and also including a working condition detection assembly, a controller, and a working condition adjustment assembly.

[0049] The operating condition detection component is used to acquire the external ambient temperature parameters and / or internal oil and gas intake pressure parameters of the separation system in real time; the operating condition adjustment component is located on the separator base assembly or the separator shaft, and the controller is used to control the operating condition adjustment component to perform internal structural change actions according to the parameters fed back by the operating condition detection component; wherein, the internal structural change actions include adjusting the axial clearance between the first separation disk and the second separation disk and / or adjusting the local temperature in the separation chamber, so as to achieve stable operation of the separation system under a predetermined low temperature environment, and maintain a preset separation efficiency under different intake conditions.

[0050] In one embodiment, the operating condition detection component includes a pressure sensor disposed at the oil-gas inlet of the separation system; the operating condition adjustment component is connected to the side of the first separation disc or the second separation disc, and is used to push and pull the corresponding separation disc axially to change the axial clearance; the controller is configured to: when the oil-gas inlet pressure detected by the pressure sensor is higher than a preset high pressure threshold, control the operating condition adjustment component to increase the axial clearance; when the oil-gas inlet pressure detected by the pressure sensor is lower than a preset low pressure threshold, control the operating condition adjustment component to decrease the axial clearance.

[0051] In one embodiment, the separator base assembly is provided with a hydraulic oil passage that connects to the lubricating oil pump of the aircraft engine, and the operating condition adjustment assembly includes a hydraulic drive sleeve or a hydraulic drive spring disposed around the first or second separator plate; the lubricating oil pressure entering the hydraulic oil passage drives the hydraulic drive sleeve or the hydraulic drive spring to move axially to change the axial clearance.

[0052] The system achieves efficient coarse and fine separation through first and second separation discs with distinct outer diameter gradients. Combined with the safety redundancy design of the pressure balance bypass regulating valve and the built-in lubricating oil return channel, the system achieves compactness and lightweight design while ensuring operational safety under extreme conditions. By utilizing an integrated architecture that combines efficient centrifugal separation, active regulation, and passive safety protection, the system effectively enhances its comprehensive adaptability to the stringent boundary constraints of aero-engines.

[0053] In one embodiment, the operating condition adjustment component includes an electromagnetic actuation component connected to the side of the first or second separation disc, which pushes or pulls the corresponding separation disc axially according to the controller's instructions.

[0054] It offers a variety of flexible clearance adjustment methods, such as electromagnetic actuation and lubricating hydraulic drive. It can use precise electronic feedback or the engine's own lubricating oil pressure to achieve delay-free follow-up adjustment. Combined with the constant centrifugal force field maintained by the independent drive of the external rotor motor, it can provide highly compatible adaptation solutions for different types of aero engines in terms of electrification level, hydraulic system characteristics and spatial layout, which greatly enhances the overall adaptability and versatility of the oil mist separation system to different engine platforms.

[0055] In one embodiment, the operating condition detection component includes a temperature sensor disposed within the separator base assembly, and the operating condition adjustment component includes an annular heating component disposed within the separator end cover or the wall of the separation chamber; when the external ambient temperature detected by the temperature sensor is lower than a preset low temperature threshold, the controller controls the annular heating component to start heating.

[0056] In one embodiment, the motor assembly is an external rotor motor, including a motor stator and a motor rotor. The motor stator is fixed inside the separator base assembly, and the motor rotor is fixed to the inner wall of the separator rotor housing and rotates synchronously with the separator shaft. The controller controls the motor assembly to operate at a preset constant speed so that the separation system has a constant centrifugal force field under any operating condition of the aero-engine.

[0057] The beneficial effects of this invention are that, through the linkage of pressure sensors, temperature sensors, and controllers, the system can actively adapt to the full range of operating conditions of an aero-engine, from idle speed to high thrust and high flow rate; simultaneously, the introduction of the annular heating component enables the system to possess thermal self-compensation capabilities in extreme low-temperature environments. Based on a real-time feedback-driven active adjustment mechanism, it overcomes the shortcomings of traditional fixed structures in handling diverse operating conditions, effectively improving the overall adaptability of the oil mist separation system to complex aero-operating environments and conditions.

[0058] The system actively increases the clearance to expand the oil-gas passage under high flow and high pressure conditions, effectively preventing the high-pressure airflow from breaking through the centrifugal oil film. Under low flow and idling conditions, it actively reduces the clearance to shorten the radial distance between the separation disk and the airflow, efficiently capturing tiny oil droplets. It also implements a bidirectional adaptive adjustment strategy for extreme flow values, ensuring that the system is always at the optimal separation operating point under different aerodynamic loads, effectively improving the system's wide-range adaptability to the drastic fluctuations in aero-engine flow.

[0059] (1) The present invention utilizes a motor assembly to independently drive the separator shaft, so that it maintains a preset constant high speed (e.g., 20,000 rpm) to provide a constant and sufficient centrifugal force field under any working conditions such as engine start, idling, slow speed, and cruising. This overcomes the defects of existing passive coaxial drive separators, such as insufficient centrifugal separation under low speed conditions and separation efficiency fluctuating with engine speed, so that the maximum separation efficiency can always remain stable.

[0060] (2) This invention forms a closed-loop adaptive adjustment mechanism through the working condition detection component, controller, and working condition adjustment component. It can actively adjust the axial clearance between the first and second separation discs and / or the local temperature in the separation chamber according to the real-time oil and gas intake pressure and / or the external ambient temperature. Under high pressure and high flow conditions, the axial clearance is increased and the oil and gas flow channel is expanded to prevent the high pressure airflow from breaking through the oil film ejected by centrifugation. Under low speed and low flow conditions, the axial clearance is reduced and the distance between the edge of the separation disc and the core area of ​​the airflow is shortened to improve the collection efficiency of tiny oil droplets. Heating is started in low temperature environment to avoid excessively high lubricating oil viscosity or local freezing, which would lead to unstable operation. As a result, the separation system can maintain the preset separation efficiency and operate stably in a wide temperature range and under different intake conditions.

[0061] (3) The present invention has a wide temperature adaptability and can work in the range of 55℃~150℃, especially suitable for the use requirements of low temperature environment at an altitude of 15km.

[0062] (4) The present invention has a lightweight overall structure and a small size (e.g., about 70 mm in length and about 38 mm in width). It adopts an independent modular layout, which is convenient for quick disassembly and replacement, adapts to the needs of rapid maintenance in the field, and meets the lightweight requirements of improving the thrust-to-weight ratio of small engines.

[0063] Please continue reading. Figure 1 As shown, in order to resolve the contradiction between the fixed gap separator's inability to simultaneously achieve high flow rate oil film rupture prevention and low flow rate high capture efficiency, the operating condition detection component also includes a pressure sensor (not shown in the figure) installed at the oil and gas inlet for real-time monitoring of the oil and gas inlet pressure.

[0064] The operating condition adjustment component is connected to the side of the first or second separation disc and can push or pull the corresponding separation disc axially under the command of the controller, thereby changing the axial clearance between the first and second separation discs. The controller executes the following adjustment logic based on the pressure parameters fed back by the pressure sensor: A. High-flow-rate load conditions: When the pressure sensor detects that the oil and gas intake pressure is higher than the preset high pressure threshold, the controller determines that the engine has entered a high flow load condition.

[0065] At this time, the controller controls the operating condition adjustment component to increase the axial clearance between the first separation disc and the second separation disc.

[0066] The increased gap expands the cross-sectional area of ​​the oil and gas flow channel, effectively reducing the flow velocity and local pressure difference when the airflow passes through the separation disk area. This prevents the high-speed, high-pressure airflow from breaking through the oil film that is centrifugally thrown to the outer wall, avoiding the separation of oil from being re-entrained and ensuring high separation efficiency under high flow conditions.

[0067] B. Low flow rate operation: When the pressure sensor detects that the oil and gas intake pressure is lower than the preset low-pressure threshold (e.g., when the engine is idling or slow), the controller controls the operating condition adjustment component to reduce the axial gap between the first and second separation discs.

[0068] At this time, the air intake flow is small, and the proportion of tiny oil droplets in the oil mist increases.

[0069] The reduced gap forces the airflow to pass closer to the edge of the high-speed rotating separation disk, utilizing the stronger shear and centrifugal forces near the edge to significantly improve the collection efficiency of tiny oil droplets, thus maintaining high separation performance even under low flow conditions.

[0070] C. Normal operating conditions: Under normal operating conditions between the high pressure threshold and the low pressure threshold, the controller can maintain the axial clearance at the preset nominal value, or continuously adjust the clearance size within a certain range according to pressure changes, thereby achieving dynamic optimization of separation performance.

[0071] This invention provides various specific methods for achieving axial clearance adjustment. Two preferred embodiments are listed below: Example 1: Please see Figure 1 As shown, the operating condition adjustment component uses an electromagnetic actuation component, such as a push-pull mechanism consisting of an electromagnetic coil and an armature.

[0072] The electromagnetic actuation assembly is connected to the first separation disc or the second separation disc (or the sliding sleeve connected thereto).

[0073] The controller adjusts the magnitude or direction of the current flowing into the electromagnetic coil based on the pressure signal, generating a corresponding electromagnetic force that drives the armature to move the separation disc precisely along the axial direction, thereby achieving gap adjustment.

[0074] The method offers fast response speed and high control precision.

[0075] Example 2: Please see Figure 1 As shown, the adjustment is achieved by utilizing the engine's own lubricating oil pressure.

[0076] A hydraulic oil passage is provided within the separator base assembly to draw outlet pressure oil from the aircraft engine lubricating oil pump. The operating condition adjustment assembly includes a hydraulically driven sleeve mounted around the first or second separator disc, with the sleeve axially linked to the separator disc.

[0077] The introduced lubricating oil pressure acts on the pressure surface of the hydraulically driven sleeve, generating axial thrust.

[0078] Since the outlet pressure of the engine oil pump usually increases with the increase of engine speed and load (high pressure under high flow conditions and low pressure under low flow conditions), the change in oil pressure directly drives the hydraulic drive sleeve to overcome the force of the return spring and generate different degrees of axial displacement, which in turn drives the separator disc to move, so as to realize the adaptive adjustment of axial clearance according to the working conditions.

[0079] To further improve the security and reliability of the system, the separation system may also include: The pressure balance bypass regulating valve is located on the separator base assembly.

[0080] When the internal pressure of the system exceeds the preset safety warning value due to abnormal conditions, the controller controls the valve to open, directing some of the gas directly to the exhaust port, quickly relieving pressure and protecting the internal components of the system from damage.

[0081] The lubricating oil return channel is located inside the separator base assembly. Its inlet is located at a low position near the outer wall of the first and second separator discs. It is used to collect the lubricating oil that is thrown to the outer wall and guide it back to the engine bearing lubrication line or the lubricating oil tank to realize the recycling of lubricating oil.

[0082] The separation system of this invention has a compact and lightweight overall structure and adopts an independent modular design, which facilitates rapid installation and disassembly maintenance on the outside of the aero engine, meeting the requirements of modern aero engines for high performance, high reliability and rapid maintenance.

[0083] In one embodiment, after the motor starts working, the rotor housing rotates and drives the separator shaft. The motor maintains a constant high speed of 20,000 rpm to ensure that the oil mist separation effect is optimal under any operating condition.

[0084] When the oil-gas mixture first enters the inlet, it lubricates the bearing.

[0085] After being separated, the oil is thrown out by the second separating disc and flows to the bearing in the middle of the separator for lubrication.

[0086] The oil mist separator can operate in the range of 55~150℃. In particular, in the low temperature environment at an altitude of 15km, the temperature of 80~90℃ carried by the lubricating oil when lubricating the bearing, combined with the heat generated by the high-speed rotating motor, ensures that the motor can operate stably.

[0087] Compared to separation driven by an engine main shaft, which has low separation efficiency at low engine starting speeds, separation efficiency is maintained at a high speed of 20,000 rpm when driven by an electric motor, ensuring that the maximum separation efficiency remains constant.

[0088] It has a wide temperature adaptability, can withstand high temperatures of 150℃ and low temperatures of 55℃, meeting the requirements of the engine during high-altitude flight.

[0089] Lightweight and compact, measuring 70mm in length and 38mm in width, it is easy to disassemble and replace.

[0090] The technical solution of the present invention has been described above with reference to the preferred embodiments shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the scope of protection of the present invention is obviously not limited to these specific embodiments. Without departing from the principles of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of the present invention.

[0091] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An oil and mist separation system for an aircraft engine, comprising: Separator base assembly and separator end cap connected to the separator base assembly; A separator shaft is axially disposed within the separator base assembly; Motor assembly for driving the separator shaft to rotate; A first separation disk and a second separation disk are disposed on the separator shaft and arranged in parallel, wherein the outer diameter of the first separation disk is larger than the outer diameter of the second separation disk; Its features include a condition detection component, a controller, and a condition adjustment component; The operating condition detection component includes a pressure sensor installed at the oil and gas inlet of the separation system, used to acquire the oil and gas inlet pressure parameters of the separation system in real time. The operating condition adjustment component is disposed on the separator base assembly or the separator shaft and connected to the side of the first separator disc or the second separator disc, and is used to push and pull the corresponding separator disc along the axial direction to change the axial clearance between the first separator disc and the second separator disc; The controller is electrically connected to the pressure sensor and the operating condition adjustment component, and is configured as follows: When the oil and gas intake pressure detected by the pressure sensor is higher than the preset high pressure threshold, the operating condition adjustment component is controlled to increase the axial clearance to expand the oil and gas flow channel. When the oil and gas intake pressure detected by the pressure sensor is lower than the preset low pressure threshold, the operating condition adjustment component is controlled to reduce the axial clearance, so as to shorten the distance between the edge of the separation disc and the core area of ​​the airflow.

2. The lubricating oil and mist separation system for an aero-engine according to claim 1, characterized in that, The separator base assembly is provided with a hydraulic oil passage that connects to the lubricating oil pump of the aircraft engine. The operating condition adjustment component includes a hydraulic drive sleeve or a hydraulic drive spring disposed around the first separation plate or the second separation plate; The lubricating oil pressure entering the hydraulic oil channel drives the hydraulic drive sleeve or the hydraulic drive spring to move axially, thereby changing the effective axial separation gap between the first separation disc and the second separation disc.

3. The lubricating oil and mist separation system for an aero-engine according to claim 2, characterized in that, The operating condition adjustment component includes an electromagnetic actuation component connected to the side of the first or second separation plate, which pushes or pulls the corresponding separation plate axially according to the instructions of the controller.

4. The lubricating oil and mist separation system for an aero-engine according to claim 3, characterized in that, The operating condition detection component includes a temperature sensor disposed within the separator base assembly, and the operating condition adjustment component includes an annular heating component disposed inside the end cover of the separator base assembly or within the wall of the separation chamber. When the external ambient temperature detected by the temperature sensor is lower than a preset low temperature threshold, the controller controls the annular heating assembly to start heating; The separator base assembly is provided with a hydraulic oil channel that connects to the lubricating oil pump of the aircraft engine. The operating condition adjustment assembly includes a hydraulic drive sleeve or a hydraulic drive spring located around the first or second separator plate. The lubricating oil pressure entering the hydraulic oil channel drives the hydraulic drive sleeve or hydraulic drive spring to move axially, thereby changing the effective axial separation gap between the first separation disc and the second separation disc.

5. The lubricating oil and mist separation system for an aero-engine according to claim 3, characterized in that, The operating condition detection component includes a pressure sensor located at the oil and gas inlet of the separation system. When the pressure sensor detects that the oil and gas intake pressure is higher than the preset high pressure threshold, and the system is determined to enter a high flow load condition, the controller controls the condition adjustment component to increase the axial gap between the first separation disc and the second separation disc, so as to expand the oil and gas flow channel and prevent the high pressure airflow from breaking through the oil film thrown out by centrifugation.

6. The lubricating oil and mist separation system for an aero-engine according to claim 3, characterized in that, When the operating condition detection component detects that the engine is idling or slow low flow condition, the controller controls the operating condition adjustment component to reduce the axial gap between the first separation disc and the second separation disc, so as to shorten the distance between the edge of the separation disc and the core area of ​​the airflow and improve the collection efficiency of tiny oil droplets.

7. The lubricating oil and mist separation system for an aero-engine according to any one of claims 4 and 6, characterized in that, The motor assembly is an external rotor motor, including a motor stator and a motor rotor. The motor stator is fixed inside the separator base assembly, and the motor rotor is fixed to the inner wall of the separator rotor housing and rotates synchronously with the separator shaft. The controller controls the motor assembly to operate at a preset constant speed so that the separation system has a constant centrifugal force field under any operating condition of the aero-engine.

8. The lubricating oil and mist separation system for an aero-engine according to claim 7, characterized in that, The first separator is located at the front end of the air intake direction, the second separator is located at the rear end of the first separator, and the outer diameter of the first separator is larger than the outer diameter of the second separator.

9. The lubricating oil and mist separation system for an aero-engine according to claim 8, characterized in that, The separation system also includes a pressure balance bypass regulating valve located on the separator base assembly. When the internal pressure of the system exceeds a preset safety warning value, the controller controls the pressure balance bypass regulating valve to open, diverting some gas to the exhaust port to maintain the stability of the internal structural pressure.

10. The lubricating oil and mist separation system for an aero-engine according to claim 9, characterized in that, The separator shaft is provided with an oil-gas mixing channel, and the separator base assembly is provided with a lubricating oil return channel. The inlet of the lubricating oil return channel is close to the outer wall of the first and second separator discs, and is used to collect the thrown-out oil and guide it to the bearing lubrication pipeline of the aero-engine.

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