A multi-model aircraft engine oil seal control device and system

Abstract

This invention discloses a multi-model aircraft engine oil seal control device and system, relating to the field of aviation support equipment technology. It includes: a multi-model aircraft engine oil seal control device, an oil supply device, and a lubricating oil dehydration supply device. The lubricating oil dehydration supply device dehydrates the lubricating oil and transmits the dehydrated oil through a pipeline to the oil tank inside the oil supply device for storage. The oil tank inside the oil supply device is connected to the oil pipe interface panel of the multi-model aircraft engine oil seal control device. The dehydrated lubricating oil, after passing through a pressure control subsystem, is delivered to the engine requiring oil sealing via the oil pipe interface panel. The pressure control subsystem includes three oil circuits, with the oil circuit selected according to the engine model. The multi-model aircraft engine oil seal control device controls the engine's cold operation via an operation panel, performing engine oil sealing during the cold operation process. This invention enables oil sealing of different engine models within the same system.

Description

Technical Field

[0001] This invention relates to the field of aviation support equipment technology, and more specifically to an oil seal control device and system for multiple types of aircraft engines. Background Technology

[0002] Currently, the engine oil sealing system is used to provide lubricating oil that meets the requirements of pressure, flow rate, temperature, contamination level, and moisture content for the fuel systems of XX-10 series and XX series aircraft engines, and to perform oil sealing, opening, nitrogen purging, and oil removal for various fuel subsystems of the engine.

[0003] Currently, there is no systematic and unified standard for the development of engine oil sealing systems among various manufacturers. As a result, the products developed by each manufacturer have strong aircraft-specific characteristics. Although each product can meet the oil sealing operation requirements of the aircraft, they are not interchangeable between similar aircraft models or even aircraft of the same series. The lack of universal and serialized design makes it difficult to guarantee oil sealing operations for multiple aircraft types.

[0004] Therefore, how to perform oil sealing on different engine models within the same system is a problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, the present invention provides a multi-model aircraft engine oil seal control device and system to solve the problems existing in the background art.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A multi-model aircraft engine oil seal control device includes: an information acquisition subsystem, a power supply system, a main control system, a pressure control subsystem, an operation panel, an oil pipe interface panel, and a cable interface panel. The power supply system is connected to the main control system and the engine via the cable interface panel, providing power to both systems. The operation panel is sequentially connected to the main control system via wiring. The main control system is signal-connected to the pressure control subsystem. The pressure control subsystem is connected to the oil pipe interface panel, which is connected to the fuel tank via wiring. It receives oil from the fuel tank, provides oil seal pressure through the pressure control subsystem, and then outputs pressurized oil for oil sealing via the oil pipe interface panel. The pressure control subsystem includes a main fuel system oil seal circuit, a high-pressure auxiliary oil seal circuit, and a lubricating oil system oil seal circuit, which are independent of each other and selected according to the engine model. The information acquisition subsystem collects engine data and transmits it to the main control system, displaying it on the operation panel.

[0008] Preferably, it also includes casters, which are installed at the bottom of the multi-model aircraft engine oil seal control device, and the casters assist the movement of the multi-model aircraft engine oil seal control device.

[0009] Preferably, the control panel includes a DC voltmeter, a DC ammeter, an AC voltmeter, a fuel seal pressure indicator I, a fuel seal pressure indicator II, a lubricating oil seal pressure indicator, an AC power indicator, a 27V power indicator, a 5V power indicator, a start-up boost indicator, an oil seal engine model status light box, a voltage selection switch, a stop button, a DC power switch, an emergency stop button, a computer switch, a start button, and a reset button. The DC voltmeter and DC ammeter monitor the voltage and current values ​​of the power system in real time; the AC voltmeter monitors the voltage value of the AC power supply connected to the engine; the fuel seal pressure indicator I and fuel seal pressure indicator II respectively display the main fuel seal oil circuit and the high-pressure auxiliary fuel seal pressure in real time. The system includes: real-time pressure values ​​of the oil seal circuit; a real-time pressure indicator for the lubricating oil seal circuit; a voltage selection switch for switching the voltage levels of the power system, displayed via 27V and 5V power indicator lights; a stop button for stopping all system operations in an emergency; a DC power switch for controlling the on / off state of the DC power supply; an AC power indicator light displaying the status of the AC power supply connected to the engine; a computer switch for controlling the start / stop of the main control system; a start button and a reset button for starting the oil seal program and restarting the main control system; a start-up voltage boost indicator light illuminating to indicate that the generator is boosting voltage; and an oil seal engine model status light box displaying the currently selected engine model.

[0010] Preferably, the oil pipe interface panel includes a lubricating oil system oil seal connector, a main oil seal connector, an auxiliary oil seal connector I, an auxiliary oil seal connector II, a lubricating oil system oil seal inlet connector, a fuel system oil seal inlet connector I, and a fuel system oil seal inlet connector II. The lubricating oil system oil seal connector is connected to the lubricating oil system oil seal circuit to inject dehydrated lubricating oil into the engine. The main oil seal connector is connected to the fuel system main oil seal circuit. Both auxiliary oil seal connector I and auxiliary oil seal connector II are connected to the high-pressure auxiliary oil seal circuit, supporting parallel oil supply. The lubricating oil system oil seal inlet connector receives oil that overflows or circulates during the oil sealing process. Both fuel system oil seal inlet connector I and fuel system oil seal inlet connector II are connected to the fuel supply source.

[0011] Preferably, the cable interface panel includes: an engine negative terminal 1 connector, an engine negative terminal 2 connector, a power supply 1 positive terminal connector, a power supply 1 negative terminal connector, a power supply 2 positive terminal connector, a power supply 2 negative terminal connector, an engine positive terminal connector, and an excitation connector. The engine negative terminal 1 connector and the engine negative terminal 2 connector are connected to the engine negative terminal portion; the power supply 1 positive terminal connector, the power supply 1 negative terminal connector, the power supply 2 positive terminal connector, and the power supply 2 negative terminal connector are respectively connected to the power supply system; the engine positive terminal connector is connected to the engine positive terminal; and the excitation connector is connected to the engine excitation device.

[0012] A multi-model aircraft engine oil seal control system includes: a multi-model aircraft engine oil seal control device, an oil supply device, and a lubricating oil dehydration supply device. The lubricating oil dehydration supply device dehydrates the lubricating oil and transmits the dehydrated lubricating oil through a pipeline to the oil tank inside the oil supply device for storage. The oil tank inside the oil supply device is connected to the oil pipe interface panel of the multi-model aircraft engine oil seal control device. After dehydration, the lubricating oil is delivered to the engine requiring oil sealing through the oil pipe interface panel after passing through a pressure control subsystem. The multi-model aircraft engine oil seal control device controls the engine to run cold through an operation panel and performs engine oil sealing during cold operation.

[0013] Preferably, it also includes: an oil seal spare parts cabinet, which is used to store the oil filling connection pipes, connectors and connection control wires of the corresponding engine model.

[0014] As can be seen from the above technical solution, compared with the prior art, the present invention discloses a multi-type aero-engine oil seal control device and system, which replaces the function of the actual engine automatic start device with the main control system, realizes "cold operation" of the engine in the off-air state, completes the oil seal control of various types of aero-engines, provides technical support for the development of integrated engine oil seal equipment, and has strong practical value. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0016] Figure 1 A block diagram showing the basic components of the oil seal control device provided by the present invention;

[0017] Figure 2a This is a front view of the multi-model aircraft engine oil seal control device provided by the present invention; Figure 2b Side view of the multi-model aircraft engine oil seal control device provided by the present invention; Figure 2c Top view of the multi-model aircraft engine oil seal control device provided by the present invention;

[0018] Figure 3 This is a diagram of the operation panel of the oil seal control device provided by the present invention;

[0019] Figure 4 A schematic diagram of the cable interface panel provided by the present invention;

[0020] Figure 5A schematic diagram of the cable interface panel provided by the present invention;

[0021] Figure 6 The schematic diagram of the starting control system provided by the present invention;

[0022] Figure 7 The software system module composition and calling principle diagram provided by this invention;

[0023] Figure 8 The circuit structure diagram of the signal acquisition system provided by this invention;

[0024] Figure 9 A simplified program execution flowchart provided for this invention;

[0025] Figure 10 The flowchart of the multi-threaded application program for the off-machine start-up control system provided by this invention;

[0026] Figure 11 The basic working principle diagram of the integrated oil seal device for engines provided by this invention;

[0027] Figure 12 This is a schematic diagram of the oil circuit system I provided by the present invention;

[0028] Figure 13 This is a schematic diagram of the oil circuit system II provided by the present invention;

[0029] Figure 14 This is a schematic diagram of the oil circuit system III provided by the present invention;

[0030] Figure 15 The engine cold-run control program flowchart provided by the present invention;

[0031] Figure 16 The control principle diagram provided for this invention;

[0032] Among them, 1-caster wheel; 2-main control computer; 3-control circuit board; 4-boost oil circuit; 5-operation panel; 6-oil pipe interface panel; 7-cable interface panel. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] This invention discloses a multi-model aero-engine oil seal control device, such as... Figure 1As shown, it includes: an information acquisition subsystem, a power supply system, a main control system, a pressure control subsystem, an operation panel, an oil pipe interface panel, and a cable interface panel. The power supply system connects the main control system and the engine through the cable interface panel, providing power to both systems. The operation panel is sequentially connected to the main control system's wiring. The main control system is connected to the pressure control subsystem via signal connections. The pressure control subsystem is connected to the oil pipe interface panel, which in turn is connected to the fuel tank's wiring. It receives fuel from inside the tank, provides oil seal pressure through the pressure control subsystem, and then outputs pressurized fuel through the oil pipe interface panel for oil sealing. The pressure control subsystem includes the main fuel system oil seal circuit, the high-pressure auxiliary oil seal circuit, and the lubricating oil system oil seal circuit, all of which are independent of each other and selected according to the engine model. The information acquisition subsystem collects engine data and transmits it to the main control system, displaying it on the operation panel.

[0035] In one specific embodiment, the structural shape of the multi-model aircraft engine oil seal control device is as follows: Figure 2a , Figure 2b and Figure 2c As shown, a caster wheel mechanism is installed at the bottom of the cabinet for ground movement. Inside the cabinet is a main control system, an information acquisition subsystem, and three pressurized oil circuits (pressure control subsystems). Both the information acquisition and pressure control subsystems are connected to the main control computer. The oil seal control device is the control center of the engine's integrated oil seal equipment. Using an industrial control computer as its core and an advanced software operating system as its control platform, it replaces the actual aircraft systems and component status control and monitoring, realizing oil seal pressure control and cold-run control during the engine's oil seal operation and opening process in the off-air condition. The oil seal control device is crucial for achieving oil seal control in the off-air condition of the engine.

[0036] The device also includes an operation panel connected to the main control computer and control circuit board, such as... Figure 3As shown. The right side is a touchscreen display, and the left side displays: a DC voltmeter, a DC ammeter, an AC voltmeter, fuel seal pressure indicator I, fuel seal pressure indicator II, lubricating oil seal pressure indicator, AC power indicator, 27V power indicator, 5V power indicator, start-up boost indicator, oil seal engine model status light box, voltage selection switch, stop button, DC power switch, emergency stop button, computer switch, start button, and reset button. The DC voltmeter and DC ammeter monitor the voltage and current values ​​of the power system in real time; the AC voltmeter monitors the voltage value of the AC power supply connected to the engine; fuel seal pressure indicator I and fuel seal pressure indicator II respectively display the main fuel level in the fuel system in real time. The system includes: real-time pressure values ​​for the oil sealing circuit and the high-pressure auxiliary oil sealing circuit; a lubricating oil seal pressure indicator that displays the real-time pressure value of the lubricating oil system's oil seal circuit; a voltage selection switch for switching the power system's voltage level, indicated by a 27V power indicator and a 5V power indicator; a stop button to stop all system operations in an emergency; a DC power switch to control the on / off state of the DC power supply; an AC power indicator that displays the status of the AC power supply connected to the engine; a computer switch to control the main control system's on / off state; a start button and a reset button for starting the oil seal program and restarting the main control system; a start-up boost indicator that illuminates indicates the generator is boosting voltage; and an oil seal engine model status light box that displays the currently selected engine model.

[0037] The device also includes an oil pipe interface panel that connects to the engine oil seal accessory, such as Figure 4 As shown. From top to bottom, they are: lubricating oil system oil seal connector, main oil seal connector, auxiliary oil seal connector I, auxiliary oil seal connector II, lubricating oil system oil seal inlet connector, fuel system oil seal inlet connector I, and fuel system oil seal inlet connector II. The lubricating oil system oil seal connector connects to the lubricating oil system oil seal circuit, injecting dehydrated lubricating oil into the engine; the main oil seal connector connects to the fuel system main oil seal circuit; auxiliary oil seal connectors I and II both connect to the high-pressure auxiliary oil seal circuit, supporting parallel oil supply; the lubricating oil system oil seal inlet connector receives oil overflowing or circulating during the sealing process; fuel system oil seal inlet connectors I and II both connect to the fuel supply source. The cable interface panel is shown below. Figure 5 As shown, from left to right, they are: Engine negative terminal 1 connector, Engine negative terminal 2 connector, Power supply 1 positive terminal connector, Power supply 1 negative terminal connector, Power supply 2 positive terminal connector, Power supply 2 negative terminal connector, Engine positive terminal connector, and Excitation connector. Engine negative terminal 1 connector and Engine negative terminal 2 connector are connected to the engine negative terminal; Power supply 1 positive terminal connector, Power supply 1 negative terminal connector, Power supply 2 positive terminal connector, and Power supply 2 negative terminal connector are respectively connected to the power system; Engine positive terminal connector is connected to the engine positive terminal; Excitation connector is connected to the engine excitation device.

[0038] The main control system is the core of the oil seal control console. It can automatically generate commands to control the oil seal pressure, flow rate, and engine cold-running procedures according to the oil seal requirements of different engines. The main control system mainly consists of a main control computer, a signal acquisition and processing unit, and an interface control unit.

[0039] The starting control system, based on instructions from the main control system, can supply the required oil type, pressure, and flow rate for different engine oil seal types, and control the cold start procedure. Simultaneously, it feeds back the engine's operating status to the main control system in real time to monitor the oil seal status and adjust the oil supply system's operation as needed, ensuring that the output pressure and flow rate meet the oil seal process requirements. The principle of the starting control system is as follows: Figure 6 As shown.

[0040] The pressure control subsystem is mainly used to meet the oil seal pressure and flow requirements of different engine models. It is designed with three oil circuits: the main oil seal circuit of the fuel system, the high-pressure auxiliary oil seal circuit, and the oil seal circuit of the lubricating oil system. The maximum pressure is 1.3MPa and the minimum pressure is 0.09MPa, which can meet the requirements of various engine models for oil seal fluid and oil seal pressure.

[0041] Engine speed control is a fundamental requirement for engine oil seals and must meet the requirements of the engine oil seal process; otherwise, the expected oil seal effect will not be achieved, and the engine may even be damaged. Since oil-sealed engines are generally stored for extended periods, their starting characteristics vary considerably. Therefore, an engine speed extraction circuit is used to collect engine speed data, transmit it to the main control computer, and process it accordingly to achieve optimal engine speed control.

[0042] Controlling the flow rate of the oil seal fluid is crucial for engine oil seals. Excessive fluid flow will damage internal engine seals, rubber gaskets, and other components; insufficient flow will prevent the oil seal fluid from fully filling the engine and its components, thus failing to achieve the desired sealing effect. Therefore, a signal acquisition circuit collects the fluid flow signal, which, after signal conditioning, is sent to the main control computer. The main control computer then controls the metering switch on the oil pump regulator according to the control program to adjust the oil seal fluid supply, ensuring the optimal flow rate.

[0043] To meet the oil seal pressure requirements of various engine models, the oil tanks need to be pressurized. Each oil tank is equipped with a pressurization system that automatically increases the pressure of the oil seal fluid according to the pressure requirements of the engine being sealed. The pressurization pressure is controlled by a precision regulating valve, and pressurization stops when the pressure reaches the specified value required for that engine model. Then, the main control system on the oil seal control panel controls the opening and closing of the oil supply solenoid valve via a computer program, thereby controlling the oil seal pressure and oil supply sequence. The control principle for oil seal pressure and oil supply sequence is as follows: Figure 16 As shown.

[0044] The power supply system is used to meet the power requirements of components such as the booster pump, solenoid valves, relays, contactors, and signal conditioning boards inside the oil seal control console. In addition, the voltage and current fluctuate significantly during engine cold operation. To ensure the normal operation of engine accessories and achieve optimal oil sealing performance, a separate power supply is provided for these accessories, preventing them from being affected by voltage fluctuations.

[0045] In terms of software composition and principles, the software programming adopts a modular design, enhancing the system's versatility, reliability, and maintainability. The software system mainly consists of a system main control module, an engine internal oil seal module, an engine opening module, an oil seal data query module, a system self-test module, and an error prevention detection module. The software system module composition and calling principles are as follows: Figure 7 As shown.

[0046] In one specific embodiment, a caster wheel is also included, which is disposed at the bottom of the multi-model aircraft engine oil seal control device, and the caster wheel assists in the movement of the multi-model aircraft engine oil seal control device.

[0047] A multi-model aircraft engine oil seal control system includes: a multi-model aircraft engine oil seal control device, an oil supply device, and a lubricating oil dehydration supply device. The lubricating oil dehydration supply device dehydrates the lubricating oil and transmits the dehydrated lubricating oil through a pipeline to the oil tank inside the oil supply device for storage. The oil tank inside the oil supply device is connected to the oil pipe interface panel of the multi-model aircraft engine oil seal control device. After dehydration, the lubricating oil is delivered to the engine that needs oil sealing through the oil pipe interface panel after passing through a pressure control subsystem. The multi-model aircraft engine oil seal control device controls the engine to run cold through an operation panel and performs engine oil sealing during cold operation.

[0048] In one specific embodiment, it further includes: an oil seal spare parts cabinet, which is used to store the oil filling connection pipe, connector and connection control wire of the corresponding engine model.

[0049] The main function of the lubricating oil dehydration supply device is to heat the lubricating oil to remove water, thereby ensuring the quality of the oil for oil seals and preparing it for engine oil seal operation. The lubricating oil dehydration supply device is essential for oil seal operation when the engine is off-engine. The main function of the fluid supply device is to supply the engine with the various fluids required for oil seal operation. The fluid supply device is fundamental for oil seal operation when the engine is off-engine.

[0050] In one specific embodiment, the main control system consists of a main control computer and interface circuitry. The main control computer controls the operation of the entire main control system. The interface circuitry consists of input / output (I / O) boards, analog-to-digital converters (A / D, D / A) boards, communication boards, function expansion boards, and control circuits. The main control computer is the core of the entire system. To ensure strong system expandability, the system uses a KJRACK-3030J industrial control computer, which features a passive backplane structure, provides 14 ISA and 4 PCI slots, integrates a 100M network adapter, and has strong anti-interference capabilities, high reliability, and good maintainability. The signal acquisition system consists of a signal acquisition module and a signal acquisition circuit. Signal acquisition is crucial when controlling engine start-up in an off-machine state. If the signal acquisition is inaccurate or has a large error, engine control cannot be achieved. Therefore, we selected the imported 5B series isolated signal conditioning module from the United States. The 5B series modules can comprehensively condition various sensor signals (voltage, current, RTD, thermocouple, strain, frequency, etc.). When selecting a temperature module, to fully consider the sensitivity and accuracy of the temperature signal, we chose the 5B37-K-02 module for thermocouple measurement, with the following main parameters: current 30mA, input signal -100℃~+1350℃, output signal 0~+5V. When selecting a speed module, to ensure the accuracy and reliability of the speed signal, we chose the 5B45-02 module for frequency measurement, with the following main parameters: current 70mA, input signal 0~1kHz, output signal 0~+5V. This module's acquisition accuracy can reach 0.05%. The circuit structure of the signal acquisition system is as follows. Figure 8 As shown. The power supply system mainly includes a 27V regulated DC power supply, a 5V regulated DC power supply, and power cables. The 27V regulated DC power supply is a military-grade, high-quality power supply that provides a safe, reliable, and stable operating voltage for the oil seal control device.

[0051] Software Development Environment: A good software development environment is crucial for realizing the control functions of the main control system. Therefore, the research group analyzed and compared several commonly used software development environments, such as VC++, VB, Delphi, Borland C++, LabVIEW, VEE, and LabWindows / CVI, ultimately choosing LabWindows / CVI. LabWindows / CVI is a software development platform for the measurement and control field launched by National Instruments. Based on ANSI C, it organically combines a powerful and flexible C language platform with professional measurement and control tools for data acquisition, analysis, and expression. Its integrated development platform, interactive programming methods, and rich controls and library functions provide an ideal software development environment for developers to build detection systems, automatic measurement environments, and data acquisition systems.

[0052] Multithreaded Programming Based on LabWindows / CVI: LabWindows / CVI offers powerful multithreaded programming capabilities. Applying multithreaded programming, placing different tasks in different threads, can bring many benefits to programming. It simplifies program development, makes program execution more efficient, and can solve many problems that single-threaded programs cannot handle. Modularizing and hierarchically dividing complex system requirements is a fundamental method of software design. The off-machine starting control system is a relatively complex system. Analysis shows it can be divided into multiple functionally independent task modules. Multiple tasks run concurrently, and each task often contains many sub-processes that need to be processed simultaneously. Figure 9 The diagram illustrates a simplified program execution flow for a typical task module of a start-up control system in an off-machine state. As can be seen, multiple tasks need to be processed simultaneously during program execution, and some tasks are subject to severe mutual exclusion. For a single-processor industrial control computer, a typical single-threaded program is clearly insufficient to implement the module's functionality. For example, when the program is in a pure delay state, no other work can be performed; if one task consumes too much CPU time, other tasks will not be executed fairly and evenly, response time cannot be guaranteed, and the system will fail to perform its intended functions.

[0053] Utilizing multithreading mechanisms in program writing is undoubtedly the best way to solve real-time multitasking software design problems. The multithreaded application flow of a start-up control system in off-site mode is as follows: Figure 10 As shown.

[0054] During program execution, the three threads—signal acquisition, signal processing, and signal transmission—operate independently. Without user intervention, each thread operates in an infinite loop, without affecting the execution of other threads. The advantages of this approach are obvious: the signal acquisition module is responsible for acquiring signals from all input channels, and the signal transmission module is responsible for transmitting signals from all output channels. Once these two modules are completed, they can be completely left unattended, allowing the user to focus on writing and debugging the signal processing module code according to different tasks. To address the issue of securely controlling the real-time data transfer between threads, the program uses the following method: two thread-safe structure variables are defined using CVI functions. These two structure variables can store all acquired or transmitted data respectively. Then, the data protection mechanisms provided by CVI are used to access these two structure variables within each thread, thus securely achieving real-time data transfer between the three threads.

[0055] The lubricating oil dehydration and supply device consists of four main parts: an oil supply system, a temperature control system, a chassis, and a power supply. The lubricating oil dehydration device is a separate enclosure with casters at the bottom for easy movement on the ground.

[0056] The oil storage tank is located in the middle of the container, heated by a reactor. It has an oil filler port and dipstick at the top, a heat transfer oil filler port on the left, and a heat transfer oil drain port on the lower right side; the bottom is the drain outlet. The power cables and control circuits are located on the left side of the forward equipment compartment; the control panel is above. The oil transfer conduit is located in the rear compartment of the container.

[0057] The fuel supply system mainly consists of a fuel supply device, a filter device, a control device, and a dedicated fuel hose, connected in sequence as follows: fuel supply device, filter device, control device, dedicated fuel hose, and fuel system oil seal inlet connector. The temperature control system mainly consists of an electric heating block, a temperature controller, an intermediate controller, a leakage current protector, and a connector, connected in sequence as follows: leakage current protector, intermediate controller, temperature controller, connector, electric heating block, and fuel supply device. The fuel supply device is equipped with a temperature sensor, which transmits the detected temperature back to the temperature controller via the connector.

[0058] The control panel of the lubricating oil dehydration device, from right to left, consists of: oil supply switch; top row: system pressure gauge, boost pressure gauge, power indicator light, heating button; bottom row: vent switch, boost switch, power switch, temperature controller.

[0059] The oil supply device is a separate box with casters at the bottom for ground movement. It mainly consists of an oil tank, an oil line adapter, and oil pipes.

[0060] The basic working principle of the engine integrated oil seal equipment is as follows: In the off-machine state, the engine is fixed on a special oil seal platform, and the engine is controlled by the oil seal control device to achieve "cold running" of the engine. When the engine rotor rotates, the lubricating oil that has been dehydrated by the lubricating oil dehydration device is injected into the inner surface of the engine fuel system accessories and lubricating oil system accessories to perform internal oil sealing of the engine.

[0061] The basic working principle of engine integrated oil seal equipment is as follows: Figure 11 As shown.

[0062] One crucial aspect of integrated oil seal equipment is ensuring the oil pressure meets the engine's sealing requirements. Statistical analysis of 30 engine models revealed the required pressures to be 0.09 MPa, 0.15 MPa, and 1.3 MPa, respectively. To guarantee these pressures, the oil circuit system was designed with three independent pressure supply systems.

[0063] The oil circuit, designed with a rated pressure of 0.09 MPa, uses an EXYB-60 explosion-proof electric oil pump as the pressure source. This system provides sufficient pressure oil to the oil seals of various engine lubrication systems. The oil circuit diagram is shown below. Figure 12 As shown.

[0064] The oil circuit, designed with a rated pressure of 0.15 MPa, uses an explosion-proof oil pump as the pressure source. This system provides sufficient pressure oil for the oil seals of various engine fuel systems. Furthermore, to meet the needs of some engines that require simultaneous main and auxiliary oil seal operation, a high-flow-rate oil pump was selected, and two parallel oil outlet connectors with the same pressure were designed. The oil circuit diagram is shown below. Figure 13 As shown.

[0065] During the statistical analysis of engine oil seal pressure, three engine models (WP-5, Piston-5, and Piston-6) required an oil seal pressure of 1.3 MPa, which ordinary oil pumps could not meet. Therefore, a plunger pump was used as the pressure source to simultaneously meet the pressure and flow requirements. In selecting the oil pump model, to ensure reliability and space utilization, the ZB-27G type oil pump (the emergency hydraulic pump for the J-7 aircraft) was chosen. Together with accumulators, pressure switches, solenoid valves, check valves, and other hydraulic accessories, it formed a high-pressure oil supply pipeline. The oil circuit diagram is shown below. Figure 14 As shown.

[0066] The working process involves the power system supplying power to the equipment, the oil supply device supplying oil to the oil pump, and the oil pump starting to work. The oil flows through a one-way valve into the accumulator, and simultaneously through a throttle valve, sensors, and hydraulic gauges. When the lubricating oil pressure increases to 13 kgf / cm³... 2When the pressure drops to zero, the sensor sends a signal to activate the solenoid valve, simultaneously stopping the hydraulic pump. The lubricating oil in the accumulator is then injected into the various subsystems of the engine oil seal through the hydraulic oil filter. When the oil pressure drops to zero, the hydraulic pump restarts, and this cycle repeats until the oil sealing process is complete.

[0067] When performing internal oil sealing on an engine, the engine needs to be cold-run, meaning the engine is only supplied with fuel and not ignited. Cold-running the engine allows the oil sealant to be injected into the engine's fuel and lubrication systems as the engine rotor rotates, thus completing the internal oil sealing process.

[0068] The engine's cold-run control is divided into two parts: one is controlling the operation, acceleration, and shutdown of the starter generator on the engine. In the "cold-run" state, the starter generator acts as an electric motor, driving the engine's high-voltage rotor and some accessories. The other part controls the on / off state of starting accessories such as the starting fuel solenoid valve, starting fuel replenishment solenoid valve, main and auxiliary fuel line vaporization solenoid valve, afterburner fuel replenishment solenoid valve, afterburner fuel solenoid valve, fuel emergency reduction solenoid valve, and low-pressure overspeed electromagnet.

[0069] The engine cold-run control is designed strictly according to the oil seal process requirements of various engine models and the engine's operating conditions, such as... Figure 15 The diagram shows the engine cold-run control program flowchart.

[0070] When the control program is working, it first opens the starter fuel supply solenoid valve to supply fuel to the main fuel pump. Next, it opens the afterburner pump solenoid valve, allowing the fuel oil to be pressurized by the afterburner pump and then sent to the afterburner combustion chamber. Then, it opens the No. 1 and No. 2 carburetor solenoid valves; after both carburetor solenoid valves are engaged, the afterburner ignition system is activated. Once a steady flow of lubricating oil is observed from the engine, the operator sends a command to the computer, and the program returns to its original state.

[0071] Taking the WJ-5 engine as an example, the process of the integrated engine oil sealing equipment completing the engine oil seal is as follows:

[0072] (1) Prepare dehydrated lubricating oil

[0073] a. Prepare fire extinguishing equipment.

[0074] b. Prepare a lubricating oil dehydration device.

[0075] c. Dehydrate the lubricating oil and lower its temperature to 60°C for later use.

[0076] (2) Prepare the engine

[0077] a. Hoist the engine onto the special oil seal platform and secure it.

[0078] b. Remove the relevant plugs and caps from the engine.

[0079] c. Connect the engine's relevant oil inlet, oil outlet, and venting connections.

[0080] (3) Prepare the oil seal control device

[0081] a. The grounding wire is reliably grounded.

[0082] b. Add oil for oil sealing to the oil tank and connect the oil tank to the "oil pump inlet connector" on the oil sealing equipment.

[0083] c. Connect the "lubricating oil system oil seal connector" and "main oil seal connector" of the oil seal equipment to the corresponding oil seal inlet connector on the engine using a hose.

[0084] d. Connect all cables and accessory cables.

[0085] e. Turn on the "Start Button", "27V" power switch, "5V" power switch and "Computer" switch in sequence.

[0086] Example 1:

[0087] I. Preparation Phase: Equipment Initialization and Connection

[0088] 1. Power supply and control device connection

[0089] Control panel:

[0090] Turn on the power switch (including 27V DC, 5V DC, and AC power switches) → AC power indicator and 27V / 5V power indicator lights up, and the power system (27V regulated power supply and 5V power supply) starts.

[0091] Cable interface panel connection:

[0092] Power supply 1 positive / negative connector, power supply 2 positive / negative connector → external stable power supply, providing independent power to engine accessories (such as starter generator).

[0093] Engine positive terminal connector and engine negative terminal 1 / 2 connector → connect to the engine starter generator circuit; excitation connector → connect to the engine excitation device.

[0094] 2. Oil circuit system connection

[0095] Oil supply device (oil tank):

[0096] Connect to the oil pipe interface panel via a dedicated oil transfer hose:

[0097] Main fuel line: fuel tank → hose → main fuel seal connector → engine fuel system main inlet.

[0098] Fuel auxiliary circuit: fuel tank → hose → auxiliary oil seal connector I / II → engine auxiliary circuit (such as afterburner).

[0099] Lubricating oil system: oil tank → hose → oil system oil seal joint → engine oil inlet.

[0100] Lubricating oil dehydration and oil supply device:

[0101] After being heated and dehydrated, the oil storage tank is connected to the oil inlet joint of the lubricating oil system via a hose to deliver dehydrated lubricating oil to the engine.

[0102] 3. Software parameter settings

[0103] Control panel touch screen:

[0104] Enter the oil seal operation interface → select the engine model (such as WJ-5), and retrieve the preset speed, pressure, and oil supply sequence parameters (stored in the main control computer).

[0105] Click the self-test button → The main control computer verifies the status of sensors (such as speed and pressure sensors) and actuators (such as solenoid valves and oil pumps) through the signal acquisition system (including 5B series modules). After the fault alarm is displayed and there are no abnormalities, it enters the ready state.

[0106] II. Execution Phase: Cold Operation and Oil Seal Operation

[0107] 1. Cold start

[0108] Start button on the control panel → The main control computer sends commands to the start control system:

[0109] When the generator is started and powered on, it acts as an electric motor to drive the engine rotor to rotate, but without ignition. The excitation connector synchronously outputs current to the excitation device to establish a magnetic field.

[0110] Speed ​​closed-loop control:

[0111] The signal acquisition system collects engine speed pulses in real time, which are then compared with the preset speed by the main control computer. The speed is kept stable by adjusting the power of the starter generator, and the speed status light on the control panel displays normally.

[0112] 2. Oil supply and pressure control

[0113] Lubricating oil system prioritizes oil supply:

[0114] Click the oil pump button → low-pressure oil pump (oil circuit control system) starts → lubricating oil flows through the pipeline → oil system oil seal joint → engine lubricating oil system, the oil seal pressure indicator shows 0.09MPa (controlled by precision regulating valve).

[0115] Fuel system with separate fuel supply lines:

[0116] Click the fuel pump button → medium-pressure fuel pump starts → fuel passes through the main fuel seal connector (main fuel line) and auxiliary fuel seal connectors I / II (auxiliary fuel line) → engine fuel system, fuel seal pressure gauge I / II displays 0.15MPa.

[0117] High pressure demand scenario: The pressure is boosted to 1.3MPa by a plunger pump (oil circuit control system), and the pressure is maintained stable by an accumulator.

[0118] Flow and stress monitoring:

[0119] The signal acquisition circuit monitors the oil flow rate in real time; the main control computer adjusts the quantitative switch of the oil pump regulator to ensure that the flow rate matches the process requirements.

[0120] When the pressure exceeds the limit, the emergency stop button will be automatically triggered, the fault alarm display will show "Pressure too high" and the oil pump power will be cut off.

[0121] 3. Fuel supply sequence and logic control

[0122] The main control computer program controls the on / off state of the solenoid valve according to a preset timing sequence:

[0123] Lubricating oil solenoid valve fully open → delay for 15 seconds → main fuel line solenoid valve opens → delay for another 10 seconds → auxiliary fuel line solenoid valve opens.

[0124] During cold operation, the display system (operation panel) displays the pressure and speed curves of each oil circuit in real time, and the operator can manually intervene.

[0125] III. End Phase: Shutdown and Equipment Reset

[0126] 1. Normal shutdown procedure

[0127] Click the Stop button → Main computer commands:

[0128] Shut down all oil pumps and solenoid valves to stop the oil supply;

[0129] When the power supply to the starter generator is cut off, the engine rotor stops rotating due to inertia, and the starter boost indicator light goes out.

[0130] Oil recovery:

[0131] Open the oil inlet connector of the lubricating oil system → return oil to the oil storage tank of the lubricating oil dehydration device, and control the recovery flow rate with the oil supply switch (operation panel of the lubricating oil dehydration device).

[0132] 2. Hardware disassembly and status restoration

[0133] Oil pipe interface panel: Disconnect the quick-release self-sealing valve to prevent oil leakage;

[0134] Cable interface panel: Disconnect the cable connected to the engine and restore the engine plug;

[0135] Control panel: Turn off the computer switch and DC power switch, the equipment will be powered off, and the power indicator light will turn off.

Claims

1. A multi-model aircraft engine oil seal control device, characterized in that, include: The system comprises an information acquisition subsystem, a power supply system, a main control system, a pressure control subsystem, an operation panel, an oil pipe interface panel, and a cable interface panel. The power supply system is connected to the main control system via the cable interface panel, providing power to the main control system. The operation panel is sequentially connected to the main control system's wiring. The main control system is signal-connected to the pressure control subsystem. The pressure control subsystem is connected to the oil pipe interface panel, which is connected to the fuel tank's wiring. It receives fuel from inside the fuel tank, provides oil seal pressure through the pressure control subsystem, and then outputs pressurized fuel for oil sealing via the oil pipe interface panel. The pressure control subsystem includes a main fuel system oil seal circuit, a high-pressure auxiliary fuel seal circuit, and a lubricating oil system oil seal circuit, which are independent of each other and selected according to the engine model. The information acquisition subsystem collects engine data and transmits it to the main control system, displaying it on the operation panel.

2. The multi-model aircraft engine oil seal control device according to claim 1, characterized in that, It also includes casters, which are installed at the bottom of the oil seal control device for multiple types of aircraft engines, and the casters assist in the movement of the oil seal control device for multiple types of aircraft engines.

3. The multi-model aircraft engine oil seal control device according to claim 1, characterized in that, The control panel includes a DC voltmeter, a DC ammeter, an AC voltmeter, a fuel seal pressure indicator I, a fuel seal pressure indicator II, a lubricating oil seal pressure indicator, an AC power indicator, a 27V power indicator, a 5V power indicator, a start-up boost indicator, an oil seal engine model status light box, a voltage selection switch, a stop button, a DC power switch, an emergency stop button, a computer switch, a start button, and a reset button. The DC voltmeter and DC ammeter monitor the voltage and current values ​​of the power system in real time; the AC voltmeter monitors the voltage value of the AC power supply connected to the engine; the fuel seal pressure indicator I and fuel seal pressure indicator II respectively display the main fuel seal oil circuit and the high-pressure auxiliary fuel in real time. The real-time pressure value of the oil seal circuit; the lubricating oil seal pressure indicator displays the real-time pressure value of the lubricating oil system's oil seal circuit; the voltage selection switch is used to switch the voltage level of the power system, and is displayed by the 27V power indicator and the 5V power indicator; the stop button is responsible for stopping all system actions in an emergency; the DC power switch controls the on / off of the DC power supply; the AC power indicator shows the status of the AC power supply connected to the engine; the computer switch controls the start / stop of the main control system; the start button and reset button are used to start the oil seal program and restart the main control system; the start boost indicator light illuminates to indicate that the generator is boosting the voltage; the oil seal engine model status light box displays the currently selected engine model.

4. The multi-model aircraft engine oil seal control device according to claim 1, characterized in that, The oil pipe interface panel includes a lubricating oil system oil seal connector, a main oil seal connector, an auxiliary oil seal connector I, an auxiliary oil seal connector II, a lubricating oil system oil seal inlet connector, a fuel system oil seal inlet connector I, and a fuel system oil seal inlet connector II. The lubricating oil system oil seal connector connects to the lubricating oil system oil seal circuit and injects dehydrated lubricating oil into the engine. The main oil seal connector connects to the main fuel system oil seal circuit. Both auxiliary oil seal connector I and auxiliary oil seal connector II connect to the high-pressure auxiliary oil seal circuit, supporting parallel oil supply. The lubricating oil system oil seal inlet connector receives oil that overflows or circulates during the oil sealing process. Both fuel system oil seal inlet connector I and fuel system oil seal inlet connector II connect to the fuel supply source.

5. The multi-model aircraft engine oil seal control device according to claim 1, characterized in that, The cable interface panel includes: engine negative terminal 1 connector, engine negative terminal 2 connector, power supply 1 positive terminal connector, power supply 1 negative terminal connector, power supply 2 positive terminal connector, power supply 2 negative terminal connector, engine positive terminal connector, and excitation connector. Engine negative terminal 1 connector and engine negative terminal 2 connector are connected to the engine negative terminal portion; power supply 1 positive terminal connector, power supply 1 negative terminal connector, power supply 2 positive terminal connector, and power supply 2 negative terminal connector are respectively connected to the power system; engine positive terminal connector is connected to the engine positive terminal; and excitation connector is connected to the engine excitation device.

6. A multi-model aircraft engine oil seal control system, employing the multi-model aircraft engine oil seal control device according to any one of claims 1-5, characterized in that, include: The system includes a multi-model aircraft engine oil seal control device, an oil supply device, and a lubricating oil dehydration supply device. The lubricating oil dehydration supply device dehydrates the lubricating oil and then transmits the dehydrated lubricating oil through a pipeline to the oil tank inside the oil supply device for storage. The oil tank inside the oil supply device is connected to the oil pipe interface panel of the multi-model aircraft engine oil seal control device. After dehydration, the lubricating oil is delivered to the engine that needs oil sealing through the oil pipe interface panel after passing through the pressure control subsystem. The multi-model aircraft engine oil seal control device controls the engine to run cold through an operation panel and performs engine oil sealing during cold operation.

7. A multi-model aircraft engine oil seal control system according to claim 6, characterized in that, Also includes: Oil seal spare parts cabinet, which is used to store the oil filling connection pipes, connectors and connection control wires of the corresponding engine model.

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