Aero-engine lubricating oil system and lubricating oil interruption processing method

Abstract

The invention provides an aero-engine lubricating oil system and a lubricating oil interruption processing method, and relates to the technical field of aero-engines. According to the aero-engine lubricating oil system, the auxiliary oil way connected with the lubricating oil tank in parallel is arranged to form the auxiliary lubricating loop, and after oil supply of the lubricating oil tank is interrupted, the lubricating oil system is switched to the auxiliary lubricating loop to achieve normal oil supply to the first oil way and the second oil way. The first compensation oil way is connected with the first oil way in parallel, the first compensation oil way is used for supplying oil to the bearing cavity in a supplementary mode under the condition that lubrication of the bearing cavity is insufficient, the second compensation oil way is connected with the second oil way in parallel, and the second compensation oil way is used for supplying oil to the gear box in a supplementary mode under the condition that lubrication of the gear box is insufficient. Due to the fact that after oil supply is interrupted, the amount of lubricating oil in the auxiliary lubricating oil way is easily lower than that in a normal working condition, dynamic and reasonable distribution of the lubricating oil can be achieved through the arrangement of the first compensation oil way and the second compensation oil way, and the lubricating requirements of the bearing cavity and the gearbox are met as much as possible.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engines, and in particular to an aircraft engine lubricating oil system and a lubricating oil interruption processing method. Background Art

[0002] The lubrication system is one of the key systems of aircraft engines. It is responsible for lubricating, cooling, cleaning and corrosion protection of the engine's main shaft bearings, bearing cavity seals, transmission system, squeeze film damper, etc. The airworthiness clause of CCAR33.71(a) stipulates that each lubrication system must be able to work normally under the flight attitude and atmospheric conditions expected to be used by the aircraft.

[0003] However, during the operation of aircraft engines, due to overload flight and lubrication system failure, the lubricating oil flow supply may be interrupted. This will lead to abnormal phenomena such as increased bearing wear, increased temperature and increased engine vibration, and even cause serious engine failure. Therefore, it is of great significance to meet the lubrication needs of aircraft engines and ensure the normal operation of aircraft engines in the event of lubricating oil interruption. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine lubricating oil system, which can meet the lubrication needs of the aircraft engine and ensure the normal operation of the aircraft engine when the lubricating oil of the aircraft engine is interrupted.

[0005] Another object of the present invention is to provide a method for handling lubricating oil interruption, which can meet the lubrication needs of the aircraft engine and ensure the normal operation of the aircraft engine when lubricating oil interruption occurs in the aircraft engine.

[0006] The embodiments of the present invention can be implemented in the following ways:

[0007] An aircraft engine lubricating oil system, comprising a lubricating oil tank, an oil supply pump, an oil supply main pipe, an oil return main pipe, a first oil circuit and a second oil circuit, wherein the oil supply pump is arranged on the oil supply main pipe, the lubricating oil tank, the oil supply main pipe, the oil return main pipe, the first oil circuit and the second oil circuit form a conventional lubrication circuit, the oil supply pump is used to pump the lubricating oil in the lubricating oil tank to the first oil circuit and the second oil circuit; the first oil circuit is connected in parallel with the second oil circuit, and the first oil circuit is used to lubricate the bearing cavity, and the second oil circuit is used to lubricate the gear box; the aircraft engine lubricating system also includes:

[0008] An auxiliary oil circuit, wherein the auxiliary oil circuit is connected in parallel with the lubricating oil tank, and the two ends are respectively connected with the oil supply main pipe and the oil return main pipe; when the oil supply of the lubricating oil tank is interrupted, an auxiliary lubrication circuit is formed through the auxiliary oil circuit, the oil supply pump, the first oil circuit and the second oil circuit;

[0009] A solenoid valve, the solenoid valve is used to control the aircraft engine oil system to switch between the conventional lubrication circuit and the auxiliary lubrication circuit;

[0010] a first compensation oil circuit, the first compensation oil circuit being connected in parallel with the first oil circuit, and the first compensation oil circuit being used to supplement oil supply to the bearing cavity when the bearing cavity is insufficiently lubricated; and

[0011] A second compensation oil circuit is connected in parallel with the second oil circuit, and the second compensation oil circuit is used to supplement oil supply to the gear box when the gear box is insufficiently lubricated.

[0012] Optionally, the aircraft engine lubricating oil system further includes an oil-gas separator, and the oil-gas separator is arranged on the auxiliary oil circuit.

[0013] Optionally, the aircraft engine lubricating oil system also includes a pressure relief oil circuit, on which a pressure relief valve is provided, and the two ends of the pressure relief oil circuit are respectively connected to the oil supply main pipe and the oil return main pipe to form a pressure relief circuit through the pressure relief oil circuit, the oil supply pump and the auxiliary oil circuit; the pressure relief valve is used to control the opening and closing of the pressure relief oil circuit.

[0014] Optionally, the aircraft engine lubricating oil system also includes a first oil pressure sensor arranged at the outlet of the oil supply pump, and the pressure relief valve is used to control the opening and closing of the pressure relief oil circuit according to the oil pressure at the outlet of the oil supply pump detected by the first oil pressure sensor.

[0015] Optionally, the first compensation oil circuit includes a front bearing cavity compensation oil circuit, a middle bearing cavity compensation oil circuit and a rear bearing cavity compensation oil circuit, and the front bearing cavity compensation oil circuit, the middle bearing cavity compensation oil circuit and the rear bearing cavity compensation oil circuit are arranged in parallel.

[0016] Optionally, the second compensation oil circuit includes an accessory gearbox compensation oil circuit and a transmission gearbox compensation oil circuit, and the accessory gearbox compensation oil circuit and the transmission gearbox compensation oil circuit are arranged in parallel.

[0017] Optionally, the aircraft engine lubricating oil system further comprises a second oil pressure sensor disposed at the lubricating oil tank, and the second oil pressure sensor is used to detect the oil pressure at the outlet of the lubricating oil tank.

[0018] A lubricating oil interruption processing method includes determining whether a lubricating oil interruption occurs in an aircraft engine;

[0019] In the event of lubricating oil interruption, the aircraft engine lubricating oil system is controlled to switch from a conventional lubricating circuit to an auxiliary lubricating circuit; the conventional lubricating circuit is supplied with oil through a lubricating oil tank, and the auxiliary lubricating circuit connects the oil supply main pipe with the oil return main pipe through an auxiliary oil circuit connected in parallel with the lubricating oil tank;

[0020] Determine the lubrication condition of the bearing cavity and gearbox;

[0021] In the case where the bearing cavity is insufficiently lubricated, the first compensation oil circuit is controlled to open to supplement the oil supply to the bearing cavity;

[0022] In the case where the gearbox is insufficiently lubricated, the second compensation oil circuit is controlled to be opened to supplement the oil supply to the gearbox.

[0023] Optionally, the aircraft engine lubricating oil system has a second oil pressure sensor for detecting the oil pressure at the lubricating oil tank outlet;

[0024] The step of determining whether the aircraft engine has oil interruption comprises:

[0025] Acquire a signal detected by the second oil pressure sensor and indicating the oil pressure at the outlet of the lubricating oil tank;

[0026] If the oil pressure at the outlet of the lubricating oil tank is lower than a preset value and lasts for a preset period of time, it is determined that the aircraft engine has an oil interruption.

[0027] Optionally, the aircraft engine lubricating oil system has a bearing outer ring temperature sensor disposed at each bearing in the bearing cavity and the gearbox and a bearing vibration sensor at each bearing;

[0028] The step of determining the lubrication conditions of the bearing cavity and the gear box comprises:

[0029] Acquiring detection signals of the bearing outer ring temperature sensor and the bearing vibration sensor;

[0030] If the bearing outer ring temperature detected by any of the bearing outer ring temperature sensors in the bearing cavity exceeds a preset value or the bearing vibration value detected by any of the bearing vibration sensors exceeds a preset value, the bearing cavity is not lubricated enough;

[0031] If the bearing outer ring temperature detected by any bearing outer ring temperature sensor in the gear box exceeds a preset value or the bearing vibration value detected by any bearing vibration sensor exceeds a preset value, the bearing cavity is not sufficiently lubricated.

[0032] Optionally, the aircraft engine lubricating oil system further includes an oil supply pump, a first oil pressure sensor and a pressure relief oil circuit; the first oil pressure sensor is used to detect the oil pressure at the outlet of the oil supply pump, and the pressure relief oil circuit, the oil supply pump and the auxiliary oil circuit form a pressure relief circuit;

[0033] The lubricating oil interruption processing method further comprises:

[0034] Acquire a signal detected by the first oil pressure sensor and indicating the oil pressure at the outlet of the oil supply pump;

[0035] When the oil pressure at the outlet of the oil supply pump exceeds a threshold value, the pressure relief oil circuit is controlled to open so that part of the lubricating oil flows directly back to the oil supply pump through the auxiliary oil circuit.

[0036] The beneficial effects of the aircraft engine lubricating oil system and lubricating oil interruption processing method provided by the embodiments of the present invention include:

[0037] The aircraft engine lubricating oil system provided by the embodiment of the present invention includes a lubricating oil tank, an oil supply pump, an oil supply pipe, an oil return pipe, a first oil circuit and a second oil circuit. The oil supply pump is arranged on the oil supply pipe, and the lubricating oil tank, the oil supply pipe, the oil return pipe, the first oil circuit and the second oil circuit form a conventional lubrication circuit. When the lubricating oil system operates normally, the lubricating oil in the lubricating oil tank is pumped to the first oil circuit and the second oil circuit through the oil supply pump. The first oil circuit is connected in parallel with the second oil circuit, and the first oil circuit is used to lubricate the bearing cavity, and the second oil circuit is used to lubricate the gear box. At the same time, the aircraft engine lubricating oil system also includes an auxiliary oil circuit, a solenoid valve, a first compensation oil circuit and a second compensation oil circuit. The auxiliary oil circuit is connected in parallel with the lubricating oil tank, and the two ends of the auxiliary oil circuit are connected to the oil supply main pipe and the oil return main pipe respectively. After the oil supply of the lubricating oil tank is interrupted, the auxiliary lubricating oil circuit is formed through the auxiliary oil circuit, the oil supply pump, the first oil circuit and the second oil circuit. The solenoid valve is used to control the lubricating oil system to switch between the conventional lubricating circuit and the auxiliary lubricating circuit. After the oil supply of the lubricating oil tank is interrupted, the lubricating oil system switches to the auxiliary lubricating circuit. The lubricating oil in the oil return main pipe enters the oil supply main pipe through the auxiliary oil circuit under the action of the oil supply pump and supplies oil to the first oil circuit and the second oil circuit, thereby realizing normal oil supply to the first oil circuit and the second oil circuit when the oil supply is interrupted. The first compensation oil circuit is connected in parallel with the first oil circuit, and the first compensation oil circuit is used to supplement the oil supply to the bearing cavity when the bearing cavity is insufficiently lubricated. The second compensation oil circuit is connected in parallel with the second oil circuit, and the second compensation oil circuit is used to supplement the oil supply to the gearbox when the gearbox is insufficiently lubricated. Since the amount of lubricating oil in the auxiliary lubricating oil circuit tends to be lower than that in normal operating conditions after the oil supply is interrupted, the provision of the first compensation oil circuit and the second compensation oil circuit can achieve dynamic and reasonable distribution of the lubricating oil to meet the lubrication needs of the bearing cavity and the gearbox as much as possible.

[0038] The lubricating oil interruption processing method provided by the embodiment of the present invention includes: judging whether the aircraft engine has a lubricating oil interruption; in the case of a lubricating oil interruption, controlling the aircraft engine lubricating oil system to switch from a conventional lubrication circuit to an auxiliary lubrication circuit; the conventional lubrication circuit supplies oil through a lubricating oil tank, and the auxiliary lubricating circuit connects the oil supply main pipe with the oil return main pipe through an auxiliary oil circuit connected in parallel with the lubricating oil tank; judging the lubrication conditions of the bearing cavity and the gearbox; in the case of insufficient lubrication of the bearing cavity, controlling the first compensation oil circuit to open to supplement the oil supply to the bearing cavity; in the case of insufficient lubrication of the gearbox, controlling the second compensation oil circuit to open to supplement the oil supply to the gearbox. In this way, in the case of a lubricating oil interruption, the aircraft engine lubricating oil system is guaranteed to continue to operate, and the dynamic and reasonable distribution of lubricating oil is realized, so as to meet the lubrication requirements of the bearing cavity and the gearbox as much as possible. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0040] Figure 1 A schematic diagram of the structure of an aircraft engine lubricating oil system according to one aspect of the present invention is shown;

[0041] Figure 2 A structural block diagram of an electric control system provided according to one aspect of the present invention is shown;

[0042] Figure 3 A partial structural schematic diagram of an aircraft engine lubricating oil system provided according to one aspect of the present invention is shown.

[0043] Reference numerals:

[0044] 100-lubricating oil system; 111-lubricating oil tank; 112-oil supply pump; 113-auxiliary oil circuit; 114-oil-gas separator; 115-pressure relief oil circuit; 116-pressure relief valve; 117-return oil pump; 118-lubricating oil radiator; 119-solenoid valve; 120-oil supply main pipe; 121-first oil supply pipe section; 122-second oil supply pipe section; 130-first oil circuit; 131-front bearing chamber oil circuit; 132-middle bearing chamber oil circuit; 133-rear bearing chamber oil circuit; 140-second oil circuit; 141-accessory gearbox oil circuit; 142-transmission gearbox oil circuit; 150-first compensation oil circuit; 151-front bearing chamber compensation oil circuit; 152-middle bearing chamber compensation oil circuit; 153-rear bearing chamber compensation oil 154-front bearing cavity compensation valve; 155-middle bearing cavity compensation valve; 156-rear bearing cavity compensation valve; 160-second compensation oil circuit; 161-accessory gearbox compensation oil circuit; 162-transmission gearbox compensation oil circuit; 163-accessory gearbox compensation valve; 164-transmission gearbox compensation valve; 170-return oil main pipe; 171-first return oil pipe section; 172-second return oil pipe section; 181-first dividing point; 182-third dividing point; 183-fourth dividing point; 191-first oil pressure sensor; 192-second oil pressure sensor; 193-third oil pressure sensor; 194-bearing outer ring temperature sensor; 195-bearing vibration sensor; 196-engine electronic controller. DETAILED DESCRIPTION

[0045] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0046] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0047] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0048] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0049] Figure 1 This is a schematic diagram of the structure of the aircraft engine lubricating oil system 100 provided in this embodiment. Figure 1 The present embodiment provides an aircraft engine lubricating oil system 100 (hereinafter referred to as the lubricating oil system 100), which includes a lubricating oil tank 111, an oil supply pump 112, an oil supply main pipe 120, an oil return main pipe 170, a first oil circuit 130, a second oil circuit 140, an auxiliary oil circuit 113, a solenoid valve 119, a first compensation oil circuit 150 and a second compensation oil circuit 160.

[0050] The oil supply pump 112 is arranged on the oil supply main pipe 120, and the oil supply main pipe 120 and the oil return main pipe 170 are both connected to the oil supply pump 112. The first oil circuit 130 and the second oil circuit 140 are connected in parallel, and the two ends of the first oil circuit 130 are respectively connected to the oil supply main pipe 120 and the oil return main pipe 170, and the two ends of the second oil circuit 140 are respectively connected to the oil supply main pipe 120 and the oil return main pipe 170. The first oil circuit 130 is used to lubricate the bearing cavity, and the second oil circuit 140 is used to lubricate the gear box. In this way, under the action of the oil supply pump 112, the lubricating oil in the lubricating oil tank 111 enters the oil supply main pipe 120, and then enters the first oil circuit 130 and the second oil circuit 140 through the oil supply main pipe 120 to achieve lubrication of the bearing cavity and the gear box; after lubricating the bearing cavity and the gear box, the lubricating oil flows into the oil return main pipe 170, and flows back to the lubricating oil tank 111 through the oil return main pipe 170; in this way, the lubricating oil tank 111, the oil supply main pipe 120, the oil return main pipe 170, the first oil circuit 130 and the second oil circuit 140 form a conventional lubrication circuit.

[0051] It should be noted that the lubrication of the lubricating oil system 100 is not limited to the bearing cavity and the gear box. If other parts of the aircraft engine also have lubrication requirements, the lubricating oil system 100 can also be provided with other oil circuits for lubricating the parts that need lubrication.

[0052] Furthermore, the lubricating oil system 100 further includes an oil return pump 117 , which is disposed on the oil return main pipe 170 . The oil return pump 117 causes the lubricating oil to flow back to the oil return main pipe 170 and flow along the oil return main pipe 170 toward the oil supply main pipe 120 .

[0053] The auxiliary oil circuit 113 is connected in parallel with the lubricating oil tank 111, and its two ends are respectively connected to the oil supply main pipe 120 and the oil return main pipe 170, so that the lubricating oil in the oil return main pipe 170 can flow back to the oil supply main pipe 120 through the auxiliary pipeline. When the oil supply is interrupted and the oil supply pump 112 cannot pump the lubricating oil in the lubricating oil tank 111 into the oil supply main pipe 120, the auxiliary pipeline can be used to form a loop for the lubricating oil without passing through the lubricating oil tank 111, that is, the auxiliary oil circuit 113, the oil supply pump 112, the first oil circuit 130 and the second oil circuit 140 can form an auxiliary lubrication circuit.

[0054] Specifically, the connection between the auxiliary oil circuit 113 and the oil supply main pipe 120 is the first dividing point 181, and the oil supply main pipe 120 is divided into a first oil supply pipe section 121 and a second oil supply pipe section 122. The end of the first oil supply pipe section 121 away from the first dividing point 181 is connected to the lubricating oil tank 111, and the end of the second oil supply pipe section 122 away from the first dividing point 181 is connected to the first oil circuit 130 and the second oil circuit 140. The oil supply pump 112 is arranged on the second oil supply pipe section 122. Similarly, the connection between the auxiliary oil circuit 113 and the oil return main pipe 170 is the second dividing point, and the oil return main pipe 170 is divided into a first oil return pipe section 171 and a second oil return pipe section 172. The end of the first oil return pipe section 171 away from the second dividing point is connected to the lubricating oil tank 111, and the end of the second oil return pipe section 172 away from the second dividing point is connected to the first oil circuit 130 and the second oil circuit 140. Therefore, the “auxiliary lubricating oil circuit” in this embodiment at least includes the second oil supply pipe section 122 , the first oil circuit 130 , the second oil circuit 140 , the second oil return pipe section 172 and the auxiliary oil circuit 113 .

[0055] The auxiliary oil circuit 113 is connected to the oil return pipe 170 through the solenoid valve 119. In other words, in this embodiment, the position of the solenoid valve 119 can be regarded as the second dividing point. The solenoid valve 119 is a two-position three-way solenoid valve 119, which controls the connection and disconnection of the second oil return pipe section 172 and the first oil return pipe section 171 and the second oil return pipe section 172 and the auxiliary oil circuit 113. Specifically, when the solenoid valve 119 controls the second oil return pipe section 172 to be connected to the first oil return pipe section 171, the second oil return pipe section 172 is disconnected from the auxiliary oil circuit 113, and the lubricating oil system 100 circulates the lubricating oil through the conventional lubricating circuit; when the solenoid valve 119 controls the second oil return pipe to be disconnected from the first oil return pipe section 171, the second oil return pipe section 172 is connected to the auxiliary oil circuit 113, and the lubricating oil system 100 circulates the lubricating oil through the auxiliary lubricating circuit.

[0056] Figure 2 The structure diagram of the electric control system provided by this embodiment is shown. Figure 1 and Figure 2Furthermore, the solenoid valve 119 is electrically connected to the engine electronic controller 196 (EEC), and the engine electronic controller 196 outputs a control signal to control the solenoid valve 119 to switch.

[0057] In this embodiment, the lubricating oil system 100 also includes an oil-gas separator 114, which is arranged on the auxiliary oil circuit 113. Therefore, when the lubricating oil system 100 is interrupted and switched to the auxiliary lubricating oil circuit, the lubricating oil in the second return oil pipe section 172 needs to be separated from the oil by the oil-gas separator 114 when passing through the auxiliary oil circuit 113 return oil supply main pipe 120.

[0058] The first compensation oil circuit 150 is connected in parallel with the first oil circuit 130 , and the first compensation oil circuit 150 is used to supplement oil supply to the bearing cavity when the bearing cavity is insufficiently lubricated.

[0059] Specifically, the first compensation oil circuit 150 is provided with a first compensation valve, and the opening and closing of the first compensation oil circuit 150 is controlled by the first compensation valve. When the lubricating oil system 100 is interrupted and switched to the auxiliary lubricating oil circuit, the lubricating oil in the auxiliary lubricating oil circuit is likely to be less than the oil amount under normal conditions, so the lubricating oil needs to be reasonably distributed. In the case of insufficient lubrication of the bearing cavity, the first compensation valve is controlled to open, and then the bearing cavity is supplied with oil through the first oil circuit 130 and the first compensation oil circuit 150, thereby providing more lubricating oil to the bearing cavity, and achieving more sufficient lubrication and cooling of the bearing cavity.

[0060] The second compensation oil circuit 160 is connected in parallel with the second oil circuit 140 , and the second compensation oil circuit 160 is used to supplement the oil supply to the gear box when the gear box is insufficiently lubricated.

[0061] Specifically, the second compensation oil circuit 160 is provided with a second compensation valve, and the opening and closing of the second compensation oil circuit 160 is controlled by the second compensation valve. When the lubricating oil system 100 is interrupted and switched to the auxiliary lubricating oil circuit, the lubricating oil in the auxiliary lubricating oil circuit is likely to be less than the oil amount under normal conditions, so the lubricating oil needs to be reasonably distributed. In the case of insufficient lubrication of the gearbox, the second compensation valve is controlled to open, and the gearbox is supplied with oil through the second oil circuit 140 and the second compensation oil circuit 160, thereby providing more lubricating oil for the gearbox, and achieving more sufficient lubrication and cooling of the bearing cavity.

[0062] Figure 3 This is a partial structural diagram of the aircraft engine lubricating oil system 100 provided in this embodiment. Figure 1-Figure 3In this embodiment, the bearing cavity includes a front bearing cavity, a middle bearing cavity and a rear bearing cavity. Accordingly, the first oil circuit 130 includes a front bearing cavity oil circuit 131, a middle bearing cavity oil circuit 132 and a rear bearing cavity oil circuit 133, and the front bearing cavity oil circuit 131, the middle bearing cavity oil circuit 132 and the rear bearing cavity oil circuit 133 are arranged in parallel. The front bearing cavity oil circuit 131 is used to supply lubricating oil to the front bearing cavity to meet the lubrication demand of the front bearing cavity; the middle bearing cavity oil circuit 132 is used to supply lubricating oil to the middle bearing cavity to meet the lubrication demand of the middle bearing cavity; the rear bearing cavity oil circuit 133 is used to supply lubricating oil to the rear bearing cavity to meet the lubrication demand of the rear bearing cavity.

[0063] The first compensation oil circuit 150 includes a front bearing cavity compensation oil circuit 151, a middle bearing cavity compensation oil circuit 152, and a rear bearing cavity compensation oil circuit 153, which are arranged in parallel. The front bearing cavity compensation oil circuit 151 is used to supplement oil supply to the front bearing cavity, the middle bearing cavity compensation oil circuit 152 is used to supplement oil supply to the middle bearing cavity, and the rear bearing cavity compensation oil circuit 153 is used to supplement oil supply to the rear bearing cavity.

[0064] Correspondingly, the first compensating valve includes a front bearing chamber compensating valve 154, a middle bearing chamber compensating valve 155 and a rear bearing chamber compensating valve 156. The front bearing chamber compensating valve 154 is arranged on the front bearing chamber compensating oil circuit 151, the middle bearing chamber compensating valve 155 is arranged on the middle bearing chamber compensating oil circuit 152, and the rear bearing chamber compensating valve 156 is arranged on the rear bearing chamber compensating oil circuit 153.

[0065] The front bearing chamber compensation valve 154 , the middle bearing chamber compensation valve 155 and the rear bearing chamber compensation valve 156 are all electrically connected to the engine electronic controller 196 , and are opened and closed under the control of the engine electronic controller 196 . Under normal circumstances, the front bearing chamber compensation valve 154, the middle bearing chamber compensation valve 155 and the rear bearing chamber compensation valve 156 are all in the normally closed state. When the lubricating oil is interrupted and switched to the auxiliary lubricating oil circuit, if the front bearing chamber is not lubricated enough, the engine electronic controller 196 controls the front bearing chamber compensation valve 154 to open, and supplies lubricating oil to the front bearing chamber through the front bearing chamber oil circuit 131 and the front bearing chamber compensation oil circuit 151; if the middle bearing chamber is not lubricated enough, the engine electronic controller 196 controls the middle bearing chamber valve to open, and supplies lubricating oil to the middle bearing chamber through the middle bearing chamber oil circuit 132 and the middle bearing chamber compensation oil circuit 152; if the rear bearing chamber is not lubricated enough, the engine electronic controller 196 controls the rear bearing chamber valve to open, and supplies lubricating oil to the rear bearing chamber through the rear bearing chamber oil circuit 133 and the rear bearing chamber compensation oil circuit 153.

[0066] In this embodiment, the gearbox includes an accessory gearbox and a transmission gearbox, and accordingly, the second oil circuit 140 includes an accessory gearbox oil circuit 141 and a transmission gearbox oil circuit 142. The accessory gearbox oil circuit 141 and the transmission gearbox oil circuit 142 are arranged in parallel, and lubricating oil is supplied to the accessory gearbox through the accessory gearbox oil circuit 141 to meet the lubrication demand of the accessory gearbox, and lubricating oil is supplied to the transmission gearbox through the transmission gearbox oil circuit 142 to meet the lubrication demand of the transmission gearbox.

[0067] The second compensation oil circuit 160 includes an accessory gearbox compensation oil circuit 161 and a transmission gearbox compensation oil circuit 162. The accessory gearbox compensation oil circuit 161 and the transmission gearbox compensation oil circuit 162 are arranged in parallel, and the accessory gearbox compensation oil circuit 161 is used to supply compensation oil to the accessory gearbox, and the transmission gearbox compensation oil circuit 162 is used to supply compensation oil to the transmission gearbox.

[0068] Correspondingly, the second compensation valve includes an accessory gearbox compensation valve 163 and a transmission gearbox compensation valve 164 . The accessory gearbox compensation valve 163 is arranged on the accessory gearbox compensation oil circuit 161 , and the transmission gearbox compensation valve 164 is arranged on the transmission gearbox compensation oil circuit 162 .

[0069] The accessory gearbox compensation valve 163 and the transmission gearbox compensation valve 164 are both electrically connected to the engine electronic controller 196 and are opened and closed under the control of the engine electronic controller 196. Under normal circumstances, the accessory gearbox compensation valve 163 and the transmission gearbox compensation valve 164 are both in a normally closed state. When the lubricating oil is interrupted and switched to the auxiliary lubricating oil circuit, if the lubrication of the accessory gearbox is insufficient, the engine electronic controller 196 controls the accessory gearbox compensation valve 163 to open, and lubricating oil is supplied to the accessory gearbox through the accessory gearbox oil circuit 141 and the accessory gearbox compensation oil circuit 161; if the lubrication of the transmission gearbox is insufficient, the engine electronic controller 196 controls the transmission gearbox compensation valve 164 to open, and lubricating oil is supplied to the transmission gearbox through the transmission gearbox oil circuit 142 and the transmission gearbox compensation oil circuit 162.

[0070] Furthermore, the lubricating oil system 100 also has a bearing outer ring temperature sensor 194 and a bearing vibration sensor 195 provided at each bearing in the bearing cavity and the gearbox, and by detecting the vibration at the bearing and the temperature of the bearing outer ring, it is determined whether there is a problem with the lubrication part of the bearing cavity and the gearbox. Specifically, the multiple bearing outer ring temperature sensors 194 and the multiple bearing vibration sensors 195 in the lubricating oil system 100 are all electrically connected to the engine electronic controller 196, and the temperature data is detected in real time through the bearing outer ring temperature sensor 194, and the vibration data is detected in real time through the bearing vibration sensor 195. If the temperature or vibration exceeds the threshold or shows a trend of continuous increase, it means that the lubrication is insufficient and more lubricating oil needs to be added.

[0071] It should be noted that the temperature or vibration threshold is confirmed based on the operating calibration value of the aircraft engine. If the data detected by the temperature sensor 194 or the bearing vibration sensor 195 of any bearing outer ring in the front bearing cavity, middle bearing cavity, rear bearing cavity, accessory gear box and transmission gear box exceeds the threshold or shows a trend of continuous increase, it means that insufficient lubrication occurs at that location. Accordingly, the engine electronic controller 196 controls the corresponding compensation valve to open.

[0072] In this embodiment, the lubricating oil system 100 also includes a pressure relief oil circuit 115, on which a pressure relief valve 116 is provided. The two ends of the pressure relief oil circuit 115 are respectively connected to the oil supply main pipe 120 and the oil return main pipe 170 to form a pressure relief circuit through the pressure relief oil circuit 115, the oil supply pump 112 and the auxiliary oil circuit 113. The pressure relief valve 116 is used to control the on and off of the pressure relief oil circuit 115.

[0073] Specifically, the pressure relief oil circuit 115 is connected to the second oil supply pipe section 122 of the oil supply main pipe 120, and the connection point between the pressure relief oil circuit 115 and the second oil supply pipe section 122 is the third dividing point 182, and the oil supply pump 112 is located between the first dividing point 181 and the third dividing point 182. The pressure relief oil circuit 115 is connected to the second oil return pipe section 172 of the oil return main pipe 170, and the connection point between the pressure relief oil circuit 115 and the second oil return pipe section 172 is the fourth dividing point 183, and the oil return pump 117 is located between the second dividing point and the fourth dividing point 183, so that when the pressure relief oil circuit 115 is opened, part of the lubricating oil pumped out from the outlet of the oil supply pump 112 directly returns to the oil return main pipe 170 through the pressure relief oil circuit 115. The pressure relief valve 116 is electrically connected to the engine electronic controller 196 , and a control signal is sent to the pressure relief valve 116 via the engine electronic controller 196 to control the opening and closing of the pressure relief valve 116 .

[0074] Furthermore, the lubricating oil system 100 also includes a lubricating oil radiator 118, which is installed on the second oil supply pipe section 122, and the lubricating oil radiator 118 is located on the side of the third dividing point 182 away from the oil supply pump 112. In other words, the lubricating oil that flows directly back to the oil return main pipe 170 from the pressure relief oil circuit 115 does not need to pass through the lubricating oil radiator 118.

[0075] Furthermore, the lubricating oil system 100 further includes a first oil pressure sensor 191 disposed at the outlet of the oil supply pump 112, and the pressure relief valve 116 is used to control the opening and closing of the pressure relief oil circuit 115 according to the oil pressure at the outlet of the oil supply pump 112 detected by the first oil pressure sensor 191. Specifically, the first oil pressure sensor 191 is disposed between the oil supply pump 112 and the third dividing point 182, so as to detect the oil pressure at the outlet of the oil supply pump 112. The first oil pressure sensor 191 is electrically connected to the engine electronic controller 196, so as to transmit a signal representing the detected oil pressure at the outlet of the oil supply pump 112 to the engine electronic controller 196. The pressure relief valve 116 is normally in a normally closed state. If the engine electronic controller 196 determines that the oil pressure exceeds the threshold value, the pressure relief valve 116 is controlled to be opened, so that part of the lubricating oil does not participate in the lubrication of the bearing cavity and the gearbox, but directly flows back to the oil return main pipe 170 from the pressure relief oil circuit 115.

[0076] In this embodiment, the lubricating oil system 100 further includes a second oil pressure sensor 192 disposed at the lubricating oil tank 111. The second oil pressure sensor 192 is used to detect the oil pressure at the outlet of the lubricating oil tank 111, so as to determine whether the lubricating oil is interrupted according to the oil pressure. Specifically, the second oil pressure sensor 192 is electrically connected to the engine electronic controller 196. The second oil pressure sensor 192 sends a signal representing the detected oil pressure at the outlet of the lubricating oil tank 111 to the engine electronic controller 196. The engine electronic controller 196 determines whether the lubricating oil system 100 has an oil interruption according to the signal. The second oil pressure sensor 192 is disposed on the first oil supply pipe section 121.

[0077] In this embodiment, the lubricating oil system 100 further includes a third oil pressure sensor 193 disposed on the auxiliary oil circuit 113, and the oil pressure value on the auxiliary oil circuit 113 is detected by the third oil pressure sensor 193 to monitor the oil pressure on the auxiliary oil circuit 113. Specifically, the third oil pressure sensor 193 is electrically connected to the engine electronic controller 196, and the oil pressure on the auxiliary oil circuit 113 detected by the third oil pressure sensor 193 can be transmitted to the engine electronic controller 196, and the engine electronic controller 196 can store or analyze the oil pressure.

[0078] The aircraft engine lubricating oil system 100 provided by the embodiment of the present invention is provided with an auxiliary oil circuit 113. In the case of lubricating oil interruption, the auxiliary lubrication circuit formed by the auxiliary oil circuit 113 can ensure the circulation of lubricating oil and realize lubrication of the bearing cavity and the gearbox. At the same time, a first compensation oil circuit 150 for lubricating oil compensation for the bearing cavity and a second compensation oil circuit 160 for lubricating oil compensation for the gearbox are also provided. The first compensation oil circuit 150 and the second compensation oil circuit 160 enable the lubricating oil to be reasonably distributed in the unconventional state of lubricating oil circulation through the auxiliary lubricating circuit to meet the lubrication demand as much as possible. The aircraft engine lubricating oil system 100 can effectively avoid general and serious mechanical failures such as bearing wear and fixture caused by reduced system oil circuit pressure and lack of oil when the lubricating oil supply is interrupted. Moreover, the aircraft engine lubricating oil system 100 does not need to make major changes to the conventional lubricating oil system 100, and does not need to add too many auxiliary equipment, so as to effectively improve the reliability and safety of the lubricating oil system 100.

[0079] The embodiment of the present invention further provides a lubricating oil interruption processing method, which can be implemented based on the above-mentioned aircraft engine lubricating oil system 100. In other words, the above-mentioned engine electronic controller 196 can be used to execute the lubricating oil interruption processing method. The lubricating oil interruption processing method includes the following steps:

[0080] S01: Determine whether the aircraft engine has oil interruption.

[0081] The engine electronic controller 196 obtains the signal indicating the oil pressure at the outlet of the lubricating oil tank 111 detected by the second oil pressure sensor 192. If the oil pressure at the outlet of the lubricating oil tank 111 is lower than a preset value and lasts for a preset time, it is determined that the aircraft engine has experienced a lubricating oil interruption. On the contrary, if the detected oil pressure at the outlet of the lubricating oil tank 111 is higher than or equal to a preset value, or the time period when it is lower than the preset value does not reach a preset time period, it is determined that the aircraft engine has not experienced a lubricating oil interruption.

[0082] Optionally, the preset value can be set to 3psid; the preset duration can be set to 3s. It is understandable that the specific value of the preset value can be adaptively adjusted according to different aircraft engine models, and accordingly, the preset duration can also be adjusted according to demand or the strictness of the judgment logic.

[0083] S02: In the event of oil interruption, the aircraft engine oil system 100 is controlled to switch from the conventional lubrication circuit to the auxiliary lubrication circuit.

[0084] If the engine electronic controller 196 determines that the lubricating oil supply to the lubricating oil system 100 is interrupted, the engine electronic controller 196 sends a control signal to the solenoid valve 119, controlling the solenoid valve 119 to disconnect the first oil return pipe section 171 from the second oil return pipe section 172, and connect the second oil return pipe section 172 to the auxiliary oil circuit 113. At this time, the lubricating oil in the second oil return pipe section 172 flows back to the oil supply main 120 through the auxiliary oil circuit 113 without passing through the lubricating oil tank 111.

[0085] S03: Determine the lubrication condition of the bearing cavity and gearbox.

[0086] The engine electronic controller 196 obtains the detection signals of multiple bearing outer ring temperature sensors 194 and bearing vibration sensors 195. If the temperature detected by any bearing outer ring temperature sensor 194 in the bearing cavity or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is judged that the bearing cavity has a problem of insufficient lubrication; if the temperature detected by any bearing outer ring temperature sensor 194 in the gear box or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is judged that the gear box has a problem of insufficient lubrication.

[0087] Specifically, if the temperature detected by any bearing outer ring temperature sensor 194 in the front bearing cavity or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is determined that the front bearing cavity has a problem of insufficient lubrication; if the temperature detected by any bearing outer ring temperature sensor 194 in the middle bearing cavity or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is determined that the middle bearing cavity has a problem of insufficient lubrication; if the temperature detected by any bearing outer ring temperature sensor 194 in the rear bearing cavity or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is determined that the rear bearing cavity has a problem of insufficient lubrication. If the temperature detected by any bearing outer ring temperature sensor 194 in the accessory gearbox or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is determined that the accessory gearbox has a problem of insufficient lubrication; if the temperature detected by any bearing outer ring temperature sensor 194 in the transmission gearbox or the vibration value detected by any bearing vibration sensor 195 exceeds the preset value, it is determined that the transmission gearbox has a problem of insufficient lubrication.

[0088] S04: When the bearing cavity is insufficiently lubricated, the first compensation oil circuit 150 is controlled to be opened to supplement the oil supply to the bearing cavity.

[0089] In the case of insufficient lubrication of the bearing cavity, the engine electronic controller 196 controls the first compensation valve to open, thereby opening the first compensation oil circuit 150. At this time, the first compensation oil circuit 150 and the first oil circuit 130 jointly supply oil to the bearing cavity.

[0090] Specifically, when the front bearing cavity is insufficiently lubricated, the engine electronic controller 196 controls the front bearing cavity compensation valve 154 to open, at which time the front bearing cavity oil circuit 131 and the front bearing cavity compensation oil circuit 151 jointly supply oil to the front bearing cavity to ensure sufficient lubrication and cooling of the front bearing cavity; when the middle bearing cavity is insufficiently lubricated, the engine electronic controller 196 controls the middle bearing cavity compensation valve 155 to open, at which time the middle bearing cavity oil circuit 132 and the middle bearing cavity compensation oil circuit 152 jointly supply oil to the middle bearing cavity to ensure sufficient lubrication and cooling of the middle bearing cavity; when the rear bearing cavity is insufficiently lubricated, the engine electronic controller 196 controls the rear bearing cavity compensation valve 156 to open, at which time the rear bearing cavity oil circuit 133 and the rear bearing cavity compensation oil circuit 153 jointly supply oil to the rear bearing cavity to ensure sufficient lubrication and cooling of the rear bearing cavity.

[0091] S05: When the gearbox is insufficiently lubricated, the second compensation oil circuit 160 is controlled to be opened to supplement the oil supply to the gearbox.

[0092] In the case of insufficient lubrication of the gearbox, the engine electronic controller 196 controls the second compensation valve to open, thereby opening the second compensation oil circuit 160. At this time, the second compensation oil circuit 160 and the second oil circuit 140 jointly supply oil to the gearbox.

[0093] Specifically, when the accessory gearbox is insufficiently lubricated, the engine electronic controller 196 controls the accessory gearbox compensation valve 163 to open, at which time the accessory gearbox oil circuit 141 and the accessory gearbox compensation oil circuit 161 jointly supply oil to the accessory gearbox to ensure sufficient lubrication and cooling of the accessory gearbox; when the transmission gearbox is insufficiently lubricated, the engine electronic controller 196 controls the transmission gearbox compensation valve 164 to open, at which time the transmission gearbox oil circuit 142 and the transmission gearbox compensation oil circuit 162 jointly supply oil to the transmission gearbox to ensure sufficient lubrication and cooling of the transmission gearbox.

[0094] It can be understood that step S04 and step S05 are steps executed corresponding to the judgment result obtained after executing step S03. Therefore, there is no restriction on the execution order of step S04 and step S05. In the actual working process, step S04 and step S05 can be executed together, or only one of them can be executed.

[0095] Furthermore, the lubricating oil interruption processing method provided by the embodiment of the present invention also includes:

[0096] S06: Obtain the oil pressure signal detected by the first oil pressure sensor 191 and indicating the outlet of the oil supply pump 112 . When the oil pressure at the outlet of the oil supply pump 112 exceeds a threshold, control the pressure relief oil circuit 115 to open.

[0097] The engine electronic controller 196 obtains the oil pressure signal detected by the first oil pressure sensor 191. If the oil pressure at the outlet of the oil supply pump 112 exceeds the threshold, the pressure relief valve 116 is controlled to open, thereby opening the pressure relief oil circuit 115. Part of the lubricating oil in the second oil supply pipe section 122 does not participate in lubrication, but directly flows from the pressure relief oil circuit 115 into the oil return pipe 170, and then flows back to the oil supply pump 112 through the oil return pipe 170 and the auxiliary oil circuit 113. It can be understood that the threshold here can be set to the oil pressure value when the lubricating oil system 100 is operating normally, and its specific data can be set according to the aircraft engine model.

[0098] Furthermore, the lubricating oil interruption processing method provided by the embodiment of the present invention also includes:

[0099] S07: If the lubricating oil system 100 resumes oil supply, the aircraft engine lubricating oil system 100 is controlled to switch from the auxiliary lubrication circuit to the normal lubrication circuit.

[0100] During the process of lubricating oil circulation of the aircraft engine lubricating oil system 100 through the auxiliary lubrication circuit, the second oil pressure sensor 192 continuously detects the oil pressure at the outlet of the lubricating oil tank 111. When the second oil pressure sensor 192 detects that the oil pressure at the outlet of the lubricating oil tank 111 returns to the normal range and lasts for a certain period of time, it is judged that the lubricating oil system 100 resumes oil supply. At this time, the engine electronic controller 196 controls the solenoid valve 119 to connect the first oil return pipe section 171 with the second oil return pipe section 172, and disconnect the second oil return pipe section 172 from the auxiliary oil circuit 113, thereby switching the aircraft engine lubricating oil system 100 from the auxiliary lubrication circuit to the conventional lubrication circuit.

[0101] It should be noted that the "normal range" referred to here is specifically set according to the type of aircraft engine. For example, the normal range can be set to be greater than 3psid, and the "certain period of time" includes but is not limited to being set to 3s.

[0102] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. An aircraft engine lubricating oil system, comprising a lubricating oil tank, an oil supply pump, an oil supply main pipe, an oil return main pipe, a first oil circuit and a second oil circuit, wherein the oil supply pump is arranged on the oil supply main pipe, the lubricating oil tank, the oil supply main pipe, the oil return main pipe, the first oil circuit and the second oil circuit form a conventional lubrication circuit, the oil supply pump is used to pump the lubricating oil in the lubricating oil tank to the first oil circuit and the second oil circuit; the first oil circuit is connected in parallel with the second oil circuit, and the first oil circuit is used to lubricate the bearing cavity, and the second oil circuit is used to lubricate the gear box; characterized in that The aircraft engine lubrication system also includes: An auxiliary oil circuit, wherein the auxiliary oil circuit is connected in parallel with the lubricating oil tank, and the two ends are respectively connected with the oil supply main pipe and the oil return main pipe; when the oil supply of the lubricating oil tank is interrupted, an auxiliary lubrication circuit is formed through the auxiliary oil circuit, the oil supply pump, the first oil circuit and the second oil circuit; A solenoid valve, the solenoid valve is used to control the aircraft engine oil system to switch between the conventional lubrication circuit and the auxiliary lubrication circuit; a first compensation oil circuit, the first compensation oil circuit being connected in parallel with the first oil circuit, and the first compensation oil circuit being used to supplement oil supply to the bearing cavity when the bearing cavity is insufficiently lubricated; and A second compensation oil circuit is connected in parallel with the second oil circuit, and the second compensation oil circuit is used to supplement oil supply to the gear box when the gear box is insufficiently lubricated.

2. The aircraft engine lubricating oil system according to claim 1, characterized in that: The aircraft engine lubricating oil system further comprises an oil-gas separator, and the oil-gas separator is arranged on the auxiliary oil circuit.

3. The aircraft engine lubricating oil system according to claim 1, characterized in that: The aircraft engine lubricating oil system also includes a pressure relief oil circuit, on which a pressure relief valve is arranged, and the two ends of the pressure relief oil circuit are respectively connected to the oil supply main pipe and the oil return main pipe to form a pressure relief circuit through the pressure relief oil circuit, the oil supply pump and the auxiliary oil circuit; the pressure relief valve is used to control the opening and closing of the pressure relief oil circuit.

4. The aircraft engine lubricating oil system according to claim 3, characterized in that: The aircraft engine lubricating oil system also includes a first oil pressure sensor arranged at the outlet of the oil supply pump, and the pressure relief valve is used to control the opening and closing of the pressure relief oil circuit according to the oil pressure at the outlet of the oil supply pump detected by the first oil pressure sensor.

5. The aircraft engine lubricating oil system according to claim 1, characterized in that: The first compensation oil circuit includes a front bearing cavity compensation oil circuit, a middle bearing cavity compensation oil circuit and a rear bearing cavity compensation oil circuit, and the front bearing cavity compensation oil circuit, the middle bearing cavity compensation oil circuit and the rear bearing cavity compensation oil circuit are arranged in parallel.

6. The aircraft engine lubricating oil system according to claim 1, characterized in that: The second compensation oil circuit includes an accessory gearbox compensation oil circuit and a transmission gearbox compensation oil circuit, and the accessory gearbox compensation oil circuit and the transmission gearbox compensation oil circuit are arranged in parallel.

7. The aircraft engine lubricating oil system according to claim 1, characterized in that: The aircraft engine lubricating oil system further includes a second oil pressure sensor disposed at the lubricating oil tank, and the second oil pressure sensor is used to detect the oil pressure at the outlet of the lubricating oil tank.

8. A method for handling lubricating oil interruption, characterized in that: The lubricating oil interruption processing method comprises: Determine whether the aircraft engine has oil interruption; In the event of lubricating oil interruption, the aircraft engine lubricating oil system is controlled to switch from a conventional lubricating circuit to an auxiliary lubricating circuit; the conventional lubricating circuit is supplied with oil through a lubricating oil tank, and the auxiliary lubricating circuit connects the oil supply main pipe with the oil return main pipe through an auxiliary oil circuit connected in parallel with the lubricating oil tank; Determine the lubrication condition of the bearing cavity and gearbox; In the case where the bearing cavity is insufficiently lubricated, the first compensation oil circuit is controlled to be opened to supplement the oil supply to the bearing cavity; In the case where the gearbox is insufficiently lubricated, the second compensation oil circuit is controlled to open to supplement the oil supply to the gearbox.

9. The lubricating oil interruption processing method according to claim 8, characterized in that: The aircraft engine lubricating oil system has a second oil pressure sensor for detecting the oil pressure at the outlet of the lubricating oil tank; The step of determining whether the aircraft engine has oil interruption comprises: Acquire a signal detected by the second oil pressure sensor and indicating the oil pressure at the outlet of the lubricating oil tank; If the oil pressure at the outlet of the lubricating oil tank is lower than a preset value and lasts for a preset period of time, it is determined that the aircraft engine has an oil interruption.

10. The lubricating oil interruption processing method according to claim 8, characterized in that: The aircraft engine lubricating oil system has a bearing outer ring temperature sensor disposed at each bearing in the bearing cavity and the gearbox and a bearing vibration sensor disposed at each bearing; The step of determining the lubrication conditions of the bearing cavity and the gear box comprises: Acquire detection signals of the bearing outer ring temperature sensor and the bearing vibration sensor; If the bearing outer ring temperature detected by any of the bearing outer ring temperature sensors in the bearing cavity exceeds a preset value or the bearing vibration value detected by any of the bearing vibration sensors exceeds a preset value, the bearing cavity is not lubricated enough; If the bearing outer ring temperature detected by any bearing outer ring temperature sensor in the gear box exceeds a preset value or the bearing vibration value detected by any bearing vibration sensor exceeds a preset value, the bearing cavity is not sufficiently lubricated.

11. The lubricating oil interruption processing method according to claim 8, characterized in that: The aircraft engine lubricating oil system further includes an oil supply pump, a first oil pressure sensor and a pressure relief oil circuit; the first oil pressure sensor is used to detect the oil pressure at the outlet of the oil supply pump, and the pressure relief oil circuit, the oil supply pump and the auxiliary oil circuit form a pressure relief circuit; The lubricating oil interruption processing method further comprises: Acquire a signal detected by the first oil pressure sensor and indicating the oil pressure at the outlet of the oil supply pump; When the oil pressure at the outlet of the oil supply pump exceeds a threshold value, the pressure relief oil circuit is controlled to open so that part of the lubricating oil flows directly back to the oil supply pump through the auxiliary oil circuit.

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