1037 results about "Fuel pump" patented technology

The invention relates to the technical field of test bed operation monitoring, in particular to a fuel pump test bed operation monitoring method and system. The method comprises the following steps: acquiring monitoring time sequence data of operation of a fuel pump test bed, performing feature extraction, constructing a coupling prediction model of a space-time diagram attention network-unscented Kalman filter, and predicting a process noise covariance matrix and a measurement noise covariance matrix according to the coupling prediction model, and performing state estimation by using an unscented Kalman filter to obtain vector posterior probability distribution, constructing a fault evolution trajectory manifold, calculating a mahalanobis distance between the vector posterior probability distribution and the fault evolution trajectory manifold, and taking the mahalanobis distance as a monitoring index. According to the scheme of the invention, the deep features which can better reflect the inherent nonlinear and complex dynamic characteristics of the system can be extracted from the multi-source data, the estimation accuracy of the filter on the potential health state of the system is improved, and the defects that model parameters are fixed and gradual change faults are difficult to capture in a traditional method are overcome.

A method of operating an aircraft gas turbine engine including: a core including a turbine, a compressor, a combustor, and a core shaft connecting the turbine to the compressor; a fan upstream of the core; a fan shaft; at least one bearing supporting the fan shaft; at least one auxiliary system using some of the fuel; an oil loop system to supply oil to the bearing; and a heat exchange system including: a primary fuel-oil heat exchanger through which oil in the oil loop system and substantially all the fuel flow to transfer heat between the oil and the fuel; and a secondary fuel-oil heat exchanger through which oil in the oil loop system and a portion of the fuel flow, to transfer heat between the oil and the fuel; and a fuel pump; wherein, under cruise conditions, fuel temperature on leaving the second heat exchanger is 120° C. to 200° C.

An aircraft fuel system includes a fuel tank, a fuel pump configured to receive a fuel flow from the fuel tank via a fuel supply line. The fuel system further includes a tap fluidly coupled to an outlet of the fuel pump, at least one generator or permanent magnet machine fluidly connected to the fuel pump via the tap, and the tap is configured to deliver fuel to the at least one generator or permanent magnet machine. The fuel system further includes a gearbox mechanically connected to the at least one generator or permanent magnet machine.

The invention relates to an aero-engine main fuel pump regulator parameter swing global closed-loop control method. The problem that at present, parameter swing faults can only be detected through engine test run is solved. According to statistical analysis of test data of an aero-engine, the rotating speed n2, P2 air pressure, S1 duty ratio and S8 duty ratio parameters of a main fuel pump regulator are controlled through a PID controller on a main fuel pump regulator performance tester under the conditions of simulating different accelerator handle angles and different temperature instruction pressures, so that actual values of follow-up piston displacement, alpha1 and alpha2 parameters are close to expected values, and the actual values of the follow-up piston displacement, alpha1 and alpha2 parameters are close to expected values. And global closed-loop control of the rotating speed and the guide vane angle is realized. The global closed-loop controller comprises an analog sampling module, an analog voltage control module, a signal control module, an upper computer module, a server module, a power supply module, an MCU module and a sensor module. According to the invention, the detection of the aero-engine parameter swing fault on the main fuel pump regulator performance tester is realized, and the occurrence of the parameter swing fault is effectively suppressed.

The invention relates to the technical field of fuel pump control, and particularly discloses an intelligent control method and system based on an intelligent integrated fuel pump, and the method comprises the steps that the intelligent integrated fuel pump is started to output fuel, and a fuel pressure sensor collects a pipeline fuel pressure signal in real time, converts the pipeline fuel pressure signal into a voltage signal and transmits the voltage signal to a CPU; the CPU presets fuel pressure values required by the engine under different working conditions, converts the received voltage signal into a fuel pressure value, compares the fuel pressure value with a set value, and generates an execution signal according to a comparison result; the processor adjusts fuel pump power supply voltage according to the execution signal and changes the rotating speed of a fuel pump motor; the PCBA temperature control module comprises a temperature sensor installed in the intelligent integrated fuel pump, and the temperature sensor senses the temperature rise condition of the PCBA in real time. Through cooperative work of the CPU, the processor and the fuel pressure sensor, accurate adjustment of the fuel pressure is achieved, and the working stability of the engine and the fuel utilization rate are improved.

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a self-adaptive supersonic speed target drone fuel oil system and a control method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, an overflow valve, a pressurization oil tank, a fuel pump, an engine pump, a monitoring module and a control module. The body fuel tank comprises a main fuel tank and an auxiliary fuel tank which are arranged in a fuel tank in the middle of the target drone body and located in front of and behind the theoretical mass center of the target drone respectively. The pressurization oil tank is additionally arranged in the fuel oil cabin, fuel oil in the engine body oil tank enters the pressurization oil tank for pressure maintaining after being pressurized by the fuel oil pump, and then oil is supplied to the engine from the pressurization oil tank, so that stable oil supply to the engine is achieved by establishing a local pressure environment instead of a large pressure environment of the whole fuel oil cabin, and therefore when a fuel oil system works, the fuel oil can be stably supplied to the engine. The oil supply flow and pressure are controlled in a closed-loop mode in real time through the control system according to the engine state.

A fuel system for a hydrogen fueled aircraft propulsion system comprises first and second hydrogen fuel tanks configured to store liquid hydrogen, first fuel line and second fuel lines configured to supply hydrogen from the first hydrogen fuel tank to a combustor of a first gas turbine engine and from the second hydrogen fuel tank to a combustor of a second gas turbine engine respectively. First and second fuel pumps are provided, each being configured to pump fuel in a respective first and second fuel line. First and second fuel heaters are provided, each being configured to heat fuel in a respective first and second fuel line. A fuel cross-feed fuel line is provided, which is configured to transfer fuel between the first and second fuel lines. The fuel cross-feed line is provided downstream in fuel flow of the first and second fuel heaters.

The invention belongs to the technical field of aero-engine control, and discloses an electric fuel pump active-disturbance-rejection control method based on a radial basis function neural network. According to the method, an intelligent control system is constructed through a radial basis function neural network, an active-disturbance-rejection controller with a nonlinear state error feedback control law as a core is designed, a control strategy is adjusted in real time according to the current state of the system, the complexity of controller parameter setting is reduced, and the stability and response speed of the system are improved. Through verification, the electric fuel pump control system obtained through the design can achieve the stable and rapid control effect under all working conditions, and is high in practicability, good in system robustness and high in anti-interference capacity.

The invention particularly relates to a parallel combination engine starting and fuel oil supply system cross-linking structure and a control method, and the parallel combination engine starting and fuel oil supply system cross-linking structure comprises an air turbine, an aircraft accessory cartridge receiver, an engine transmission system and a stamping fuel oil pump; an air turbine shaft is connected with an aircraft accessory casing, a starting clutch is arranged between the air turbine shaft and the aircraft accessory casing, the aircraft accessory casing is connected with an engine transmission system, and the engine transmission system is connected with a turbine engine; an air turbine shaft is connected with a ramjet fuel pump, an oil supply clutch is arranged between the air turbine shaft and the ramjet fuel pump, and the ramjet fuel pump is used for The air turbine is connected with an airplane auxiliary power system through an air entraining pipeline; an auxiliary air entraining valve is arranged on the air entraining pipeline; the air turbine is connected with the turbine engine fan rear flow channel through an air entraining pipeline, and a fan air entraining valve is arranged on the air entraining pipeline. The air turbine is connected with the stamping air inlet channel through an air entraining pipeline, and a stamping air entraining valve is arranged on the air entraining pipeline.

The utility model relates to an oil supply system, a power driving system and an aircraft, the oil supply system is connected with an engine and an oil tank, the oil supply system comprises an oil supply pipeline, a fuel pump and a one-way valve, and the fuel pump and the one-way valve are arranged on the oil supply pipeline between the engine and the oil tank; the multiple fuel pumps and the multiple one-way valves are arranged, the multiple fuel pumps are connected in series, the multiple one-way valves are connected in series, the fuel pumps and the one-way valves are arranged in parallel, and the multiple fuel pumps and the one-way valves are connected through oil supply pipelines. A plurality of fuel pumps and a plurality of one-way valves are arranged in series, the fuel pumps and the one-way valves are arranged in parallel, the fuel pumps and the one-way valves are communicated through oil supply pipelines, and various oil supply channels are formed between the fuel pumps and the one-way valves, so that the situation that a fuel system cannot work normally due to faults of a single fuel pump or one-way valve can be avoided; and the safety and the reliability of the oil supply system are improved.

Disclosed in the present invention is an integrated reforming power generation test system having wide-range fuel adaptability, comprising a fuel supply subsystem, a catalytic reforming subsystem, a hydrogen purification subsystem, a power generation subsystem, and a test monitoring subsystem. A fuel pump and a fuel delivery pump are connected to a water-gas shift reactor by means of an evaporator and a reformer, the water-gas shift reactor is connected to a pressure swing adsorption device by means of a first gas-liquid separator, the pressure swing adsorption device is connected to a fuel cell stack by means of a hydrogen buffer tank, and a gas chromatograph is connected to the reformer by means of a third gas-liquid separator and to the water-gas shift reactor by means of a second gas-liquid separator. By using a variety of fuel resources to produce electricity, the present invention breaks through the limitation of the scope of traditional single-fuel reforming power generation systems, ensures the reliability of electricity supply, gets rid of the dependence on specific fuels, enhances regional energy safety, and improves the flexibility of energy supply.

A retrofit gas turbine engine includes a compressor, a combustor and a turbine. A tie shaft is connected to rotate by the turbine, and provide rotational drive into a gearbox. At least one fuel pump is connected to be driven by the gearbox. The at least one fuel pump delivers fuel downstream toward the combustor, and also has a return line. An added accessory turbine is positioned on the return line, and drives an added accessory which has been retrofit added to an existing gas turbine engine. A method is also disclosed.

A method of operating a gas turbine engine of an aircraft, the gas turbine engine comprising: an engine core comprising a turbine, a compressor, a combustion chamber arranged to combust a fuel, and a core shaft connecting the turbine to the compressor; a fan arranged upstream of the engine core; a fan shaft; at least one bearing arranged to support the fan shaft; at least one auxiliary system arranged to consume a portion of the fuel; an oil circulation system arranged to supply oil to the at least one bearing; and a heat exchange system comprising: a primary fuel-to-oil heat exchanger through which the oil in the oil circulation system and at least substantially all of the fuel flow flow, such that heat is transferred between the oil and the fuel;and a secondary fuel-to-oil heat exchanger through which the oil in the oil circulation system and a portion of the fuel flow, such that heat is transferred between the oil and the fuel, wherein the secondary fuel-to-oil heat exchanger is arranged to supply fuel to the at least one auxiliary system; and a fuel pump arranged to pump the fuel, wherein the fuel pump is arranged along a fuel flow path downstream of the primary fuel-to-oil heat exchanger and upstream of the secondary fuel-to-oil heat exchanger; the method further comprising controlling the heat exchange system such that, under cruise conditions, the fuel temperature upon exiting the secondary heat exchanger is in the range of 120°C to 200°C.

A brushless motor fuel pump with a built-in controller, comprising a control unit, a brushless motor and a fuel pump connected in sequence. The control unit includes an oil outlet cover, a controller, a heat conducting pad, a mounting bracket and a metal heat sink. The mounting bracket is fixedly installed on the upper end of the brushless motor. A circulation cavity for the outflow of oil fluid is provided between the mounting bracket and the upper end of the brushless motor. The circulation cavity, the brushless motor and the fuel pump are connected in sequence. The oil outlet cover is fixedly connected to the upper end of the mounting bracket, and the oil outlet cover is provided with an oil outlet communicating with the circulation cavity. The mounting bracket and the oil outlet cover are hermetically connected to form a sealed cavity for installing the controller. The controller, the heat conducting pad and the metal heat sink are connected in sequence from top to bottom. The lower part of the metal heat sink is hermetically installed in a mounting hole provided in the mounting bracket, and the metal heat sink passes through the mounting hole and is exposed in the circulation cavity.

The invention relates to the technical field of generator fuel pump control, in particular to an energy-saving generator fuel pump optimization method and system. Comprises: continuously collecting operation parameters of a generator system, and determining whether the generator system is in a stable operation condition; after the stable operation working condition is judged, perturbation testing is executed, and the actual output pressure and the actual fuel flow of the fuel pump are obtained; calculating the performance deviation of the fuel pump, and carrying out trend analysis to identify continuous performance drift; when the trend analysis shows that continuous performance drifting exists, self-adaptive correction is conducted on the fuel pump control basis to obtain the corrected fuel pump control basis; and the corrected fuel pump control basis is applied to control operation of the fuel pump. The problems that hidden energy consumption is increased and equipment failure risks are caused when an existing generator fuel pump control system is in the face of tiny changes of fuel physical attributes and gradual degradation of the performance of a fuel pump are solved.

An in-tank fuel pump assembly and mounting system is disclosed which may be configured for mounting inside a fuel tank. The assembly includes a pump housing, pump mounted to the housing, and pressure relief valve. The housing may comprise upper and lower pump housing units coupled together. The upper housing unit is configured for mounting to a tank opening, which in one implementation may be the fuel fill opening. The lower housing unit extends into the tank to approximately the bottom of the tank. A fuel fill fluid pathway is created through the housing for adding fuel to the tank while the pump assembly remains in situ. The upper housing unit may include a removable fuel cap. The pump housing may include an integral vapor trap.

To suppress vapor lock even when vapor is generated in a fuel supply device caused by the evaporation of fuel.SOLUTION: A fuel supply device (50) comprises a fuel pump (51) delivering fuel from a fuel tank to a fuel passage, a fuel filter (54) located on the downstream side of the fuel passage further than the fuel pump, a branch joint (61) located on the downstream side of the fuel passage further than the fuel filter, and a fuel injection valve (62) injecting the fuel from the downstream end of the fuel passage to an intake passage. In the branch joint, a pair of branch pipes are provided. To one branch pipe, a return pipe (73) is connected for returning the fuel to the fuel pump, and to the other branch pipe, a feed pipe (74) is connected for guiding the fuel to the fuel injection valve. One branch pipe is located at a position higher than the position of the other branch pipe.SELECTED DRAWING: Figure 4

Disclosed is an anti-siphonage and anti-overflow fuel pump structure. The anti-siphonage and anti-overflow fuel pump structure includes a fuel pump, a fuel inlet hose, a main flow channel assembly, a control box, an exhaust and backflow channel assembly, and a fuel outlet hose, where the control box includes a housing, a battery assembly, and a control board; the main flow channel assembly includes an input channel, an output channel, an exhaust port, and a seal port; and the exhaust and backflow channel assembly includes an exhaust valve, a pipeline joint, an exhaust pipe, and an exhaust and backflow channel, the exhaust valve is arranged inside the exhaust port, the pipeline joint is arranged above the exhaust valve, one end of the exhaust pipe is connected to the pipeline joint, and the other end of the exhaust pipe is connected to the exhaust and backflow channel.

The invention discloses centering, positioning and welding equipment for motorcycle fuel pump manufacturing, and relates to the technical field of welding equipment. The centering, positioning and welding equipment for motorcycle fuel pump manufacturing comprises a supporting bottom plate, a first support, a welding shell, a centering device, a conveying device, a welding device, a discharging port and a discharging device, firstly, the supporting bottom plate provides a stable foundation, the first support is installed on the supporting bottom plate, and extra stability and supporting force are provided for the whole structure; the welding shell protects sparks and smoke generated in the welding process, and safety and cleanness of the operation environment are guaranteed. Besides, the centering device is the core technology of the whole equipment, the conveying device is responsible for conveying the parts to the welding position in order, and high-precision welding operation can be executed under calibration of the centering device. The equipment not only improves the production efficiency, but also improves the reliability and precision of products.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The invention provides a dual-fuel composite pre-cooling engine system based on jet flow / heat exchanger pre-cooling and a using method of the dual-fuel composite pre-cooling engine system, and relates to the field of aircraft engine systems. An air inlet channel, a fuel pump, a precooler, a jet device, an air compressor, a main combustion chamber, a turbine, an afterburner and an exhaust nozzle sequentially form an engine main body in the axial direction. According to the system, the characteristics of jet flow precooling and heat exchanger precooling are combined, liquid ammonia / kerosene dual-fuel layout is adopted, and a cooling working medium can realize conversion of precooling working places through a control valve according to precooling requirements, so that incoming flow air in different flight states is efficiently precooled; and the problems that a heat exchanger is large in precooling weight and flow resistance and a jet device is poor in precooling heat exchange effect are effectively solved. And finally, the system gives consideration to the simple jet flow pre-cooling structure and the high efficiency of heat exchanger pre-cooling, and the pre-cooling effect and the propelling performance of the pre-cooling engine are effectively improved.

The utility model provides a motor vehicle fuel oil system, and belongs to the technical field of motor vehicle fuel oil system structures. The motor vehicle fuel system is communicated with a fuel pump and a fuel injector component through a first fuel pipe; the second fuel pipe is communicated with the fuel injector component and the fuel tank, and the pressure release valve is mounted on the second fuel pipe, so that the problem that the fuel pipe is gasified under the influence of temperature to generate air resistance, and ignition of an engine is difficult is solved. The system comprises a fuel tank, a fuel pump, a fuel injector component and an engine, the fuel pump and the fuel injector component are connected through a fuel pipe component, the fuel pump pumps fuel in the fuel tank into the fuel injector component, the fuel enters an air cylinder of the engine under the action of the fuel injector component, and the fuel pipe component comprises a first fuel pipe and a second fuel pipe; the first fuel pipe is communicated with the fuel pump and the fuel injector component; the second fuel pipe is communicated with the fuel injector component and the fuel tank, and a pressure release valve is installed on the second fuel pipe.

A gas turbine engine is configured to combust hydrogen fuel. The gas turbine engine comprises a fuel system comprising: a fuel pump configured to provide pressurised fuel to a core combustor of the gas turbine engine; a recuperator configured to heat fuel from combustion gases downstream of the core combustor; a fuel turbine downstream in fuel flow of the recuperator. The fuel turbine being configured to be driven by heated fuel and configured to power the fuel pump. Wherein the fuel turbine has an

The invention discloses a joint simulation solving method for a fuel oil thermal management system, and the method comprises the steps: determining a heat sink model through a thermophysical parameter iteration process on an Aspen Plus platform, and calculating the thermophysical parameters of each heat sink along with the changes of temperature and pressure; in the MATLAB / Simulink platform, the storage temperature T0 and the storage pressure P0 are determined according to the physical property of the fuel oil, the mass flow of the fuel oil is solved in a circulating mode through the heat source temperature iteration process, and the heat absorbed by the fuel oil at the FADEC system, the fuel oil pump, the airborne equipment and the engine heat source and the outlet fuel oil temperature are calculated in combination with a heat source module; the heat exchanger adjusts the flow of the consumable heat sink through the heat sink flow iteration process to reduce the fuel oil to the initial temperature T0; the joint simulation platform finally solves various performance evaluation indexes of the system according to feedback results of thermophysical property parameter iteration, heat source temperature iteration and heat sink flow iteration, the coupling mechanism between the heat exchanger module and the heat sink is clarified, and the problems that a traditional modeling method is single and poor in accuracy are solved.

The invention discloses an electric fuel pump flow-rotating speed calibration and flow control method, and belongs to the field of aero-engine fuel flow control. The calibration method comprises the steps that a current fuel mass flow demand value is received; converting the fuel mass flow demand value into a fuel volume flow according to the fuel density corresponding to the current fuel temperature; and calculating the rotating speed of the motor according to the inlet pressure and outlet pressure of the electric fuel pump, the fuel temperature and the fuel volume flow. According to the method, the influence of the fuel oil density on the internal leakage rate is considered, and in the flow-rotating speed calibration calculation process, the fuel oil density is represented through the temperature T to participate in fitting of a polynomial, so that the electric fuel oil pump has flow-rotating speed calibration in a wider temperature domain range, and the actual flight environment requirement is met.

The stretching machine cooling liquid heating device suitable for the plateau environment comprises a battery bin, a power supply battery is arranged in the battery bin, an oil storage bin is arranged on one side of the battery bin, the power supply battery is electrically connected with an oil supply pump, the input end of the oil supply pump is connected to a stretching machine oil tank, and the output end of the oil supply pump is connected to the input end of the oil storage bin; the output end of the oil storage bin is connected with a fuel oil heater, the fuel oil heater comprises a combustion chamber, a heating coil is wound on the outer side of the combustion chamber, the output end of the heating coil is connected to the stretching machine water tank, the input end of the heating coil is connected with a circulating pump, a preheating bin is arranged on the outer side of the battery bin and the oil storage bin, and a self-heating bag set is arranged in the preheating bin. The fuel oil heater is arranged to heat the cooling liquid in the water tank of the stretching machine, so that when the stretching machine is in the low-temperature environment of the plateau, the engine assembly is heated through the heated cooling liquid, the starting temperature of the engine assembly is increased, and the service life of the stretching machine in the plateau environment is prolonged.

The present disclosure relates to a method for refueling a vehicle (102). The method comprises determining the vehicle (102) approaching a gas station based on location data of the vehicle (102). The method further comprises activating a side detection unit (106) of the vehicle (102) when the vehicle (102) is within a predefined proximity to a fuel pump (108) in the gas station. The method further comprises scanning a Quick Response (QR) code (112) located on a fuel nozzle (110) connected to the fuel pump (108) using the side detection unit (106) to obtain a fuel type associated with the fuel nozzle (110). Thereafter, the method comprises controlling a fuel door connected to the vehicle (102) to refuel the vehicle (102) by comparing the obtained fuel type and a predefined fuel type of the vehicle (102).

A seaplane float frame apparatus with extra fuel storage, and a method of installing, comprising: 1) a middle section housing at least one auxiliary fuel storage tank; and 2) two opposing side panels affixed to the middle section, extending outward from about 45-60-degrees from the parallel, each of the two opposing side panels comprising a bottom flat edge fit-able to a float (e.g., carbon composite). The middle section further comprises a fuel pump and a fuel line attached to the auxiliary fuel storage tank(s) and to a main fuel tank within an airplane fuselage-engine. Electrical components enable the pilot, or automatedly as needed, to pump fuel from the frame's tanks. The two opposing side panels comprise triangular shaped cutouts to reduce the float frame's weight and drag, and a built-in steps, a bar, and non-skid coating on the floats to assist in climbing safely into / out of the cockpit.

The invention provides a full-flow afterburning cycle engine double-half-system combined hot test device and a hot test method. The full-flow afterburning cycle engine double-half-system combined hot test device comprises a fuel-rich half-system test unit and an oxygen-rich half-system test unit, the fuel-rich semi-system test unit comprises a fuel-rich generator, a turbine I, a fuel pump, a fuel-rich gas process spray pipe, a guide cylinder I and a fuel inlet pipeline; the oxygen-enriched semi-system test unit comprises an oxygen-enriched generator, a turbine II, an oxygen pump, an oxygen-enriched fuel gas process spray pipe, a guide cylinder II and an oxygen inlet pipeline, the problems that the fuel side supply pressure is too high and the test difficulty is large in a single oxygen-enriched semi-system thermal test are solved, the examination working condition is not limited by the inlet pressure, and all assemblies of the semi-system can be fully examined; and meanwhile, the gas emission safety in the test process is ensured through gas emission diversion.

The invention belongs to the technical field of aircraft engine accessory casing structural design, and particularly relates to an aircraft engine accessory casing fuel pump gear shaft spline bearing lubricating structure which comprises an oil passing shaft and an adapter ring. The oil passing shaft is a hollow shaft and is arranged in the end, provided with the gear, of the gear shaft, the end of the gear shaft is sleeved with a bearing, the bearing is located on the outer side of the gear, and a spline is arranged in the other end of the gear shaft. The gear shaft is provided with a plurality of bearing lubricating channels distributed in the circumferential direction, all the bearing lubricating channels are communicated with the portion between the bearing and the gear, and all the bearing lubricating channels incline towards the bearing. The adapter ring sleeves the oil passing shaft and is connected to the inner side of the gear shaft; an annular oil collecting groove is formed in the end portion of the end, facing the spline, of the adapter ring, an annular oil collecting cavity is formed between the adapter ring and the gear shaft, the annular oil collecting groove and the annular oil collecting cavity are communicated through a plurality of oil through holes distributed in the axial direction, and the annular oil collecting cavity is communicated with the bearing lubricating channels.