Turbine aero-engine high-precision fuel metering device and method based on stepping motor and differential pressure valve

Abstract

The invention aims to improve the reliability of the fuel oil metering device of the turbine aero-engine and solve the problems that the fuel oil metering precision of the turbine aero-engine is not high and the outlet of a starting nozzle is coked. The invention discloses a high-precision fuel metering device for controlling a turbine aero-engine based on a stepping motor and a control method. The device and the method are suitable for fuel metering and control of the turbine aero-engine under all working conditions. The device is characterized by being composed of a coarse oil filter (1), a gear pump (2), a safety valve (3), an essential oil filter (4), a metering oil needle (5), a stepping motor (6), an angular displacement sensor (7), an aero-engine controller (8), a pressure sensor (9), a rotating speed sensor (10), a constant pressure difference valve (11), a main fuel oil electromagnetic valve (12), a starting fuel oil electromagnetic valve (13), a starting nozzle (14), a main fuel oil nozzle (15), a cleaning valve (16) and a gas compressor rear gas guide pipe (17). And an oil pipe (18) and a control line (19).

Description

Technical Field

[0001] The invention mainly relates to high-precision fuel metering of a turbine aircraft engine under all operating conditions and improving the coking of a starting nozzle. Background Art

[0002] The aircraft engine controller and fuel metering device are the core components of the turbine aircraft engine control system and are an important guarantee for the power of the entire turbine aircraft engine. Since the advent of aircraft engines, the fuel mechanism and control device of aircraft engines have experienced the development of fuel open-loop control to fuel closed-loop control; from hydraulic mechanical closed-loop control to full-authority electronic control; fuel metering has developed from horseshoe centrifugal flyweight speed measurement and profile hole measurement to sound wheel speed measurement. Electro-hydraulic servo valve control profile metering is currently the main method of aircraft engine fuel control. In practical applications, since the electro-hydraulic servo valve is a precision structural part, and the working environment of the aircraft engine is complex and the vibration is large, the electro-hydraulic servo valve is very easy to damage, so the reliability of electro-hydraulic servo fuel control fuel metering is poor. Summary of the invention

[0003] The invention aims to solve the problems of low fuel metering accuracy of aviation engines and coking at the outlet of starting nozzles, and further proposes a device and method for controlling the fuel flow of aviation engines based on a stepping motor.

[0004] In view of the above problems, the present invention proposes a fuel metering device based on a stepper motor and an equal pressure differential valve. At the same time, in order to improve the fuel metering accuracy, the fuel system control is further improved through the engine controller and the stepper motor control subdivision algorithm.

[0005] On the other hand, in view of the fact that the starting fuel nozzle of aircraft engines is prone to coking, a design is proposed to introduce a stream of gas from the back of the compressor. When the starting nozzle is closed, the compressor pressure opens the cleaning valve to gently blow the fuel remaining on the surface of the starting nozzle to prevent the starting nozzle from coking and clogging the nozzle, thereby ensuring reliable starting of the turbine aircraft engine.

[0006] The technical solution adopted by the present invention to solve the technical problem is: A fuel metering device for an aircraft engine controlled by a stepper motor is characterized in that the device comprises a coarse oil filter (1), a gear pump (2), a safety valve (3), a fine oil filter (4), a metering oil needle (5), a stepper motor (6), an angular displacement sensor (7), an aircraft engine controller (8), a pressure sensor (9), a speed sensor (10), an equal pressure difference valve (11), a main fuel cell valve (12), a starting fuel cell valve (13), a starting nozzle (14), a main fuel nozzle (15), a cleaning valve (16), a compressor rear air duct (17), an oil pipe (18) and a control line (19).

[0007] A high-precision fuel control device is characterized in that the device is composed of an FPGA control module (1), a power amplifier module (2), a stepper motor (3), a reducer (4), a fuel metering valve (5), an angular displacement sensor (6), etc.

[0008] The significant advantages of the present invention over the prior art are: in view of the current shortcomings of low fuel metering accuracy of aviation engines and coking at the outlet of pneumatic nozzles, this technology improves the accuracy of fuel metering of aviation engines and improves the problem of coking at the outlet of starting nozzles. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 It is a high-precision fuel metering device for aircraft engines based on a stepper motor and a pressure differential valve.

[0010] Figure 2 It is a high-precision fuel control device.

[0011] Figure 3 Break down the control logic diagram for stepper motors.

[0012] Figure 1 In the middle: 1 is the coarse oil filter, 2 is the gear pump, 3 is the safety valve, 4 is the fine oil filter, 5 is the metering oil needle, 6 is the stepper motor, 7 is the displacement sensor, 8 is the aircraft engine controller, 9 is the pressure sensor, 10 is the speed sensor, 11 is the equal pressure difference valve, 12 is the main fuel solenoid valve, 13 is the starting fuel solenoid valve, 14 is the starting nozzle, 15 is the main fuel nozzle, 16 is the cleaning valve, 17 is the compressor rear air duct, 18 is the oil pipe, and 19 is the control line.

[0013] Figure 2 In the figure: 1 is FPGA control module, 2 is power amplifier module, 3 is stepper motor, 4 is reducer, 5 is fuel metering valve and 6 is angular displacement sensor. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solution and advantages of the present application more clear, the embodiments of the present application will be described in detail below. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other arbitrarily without conflict.

[0015] The present application is further described in detail below in conjunction with specific examples, but the examples should not be construed as limiting the present application.

[0016] Aircraft engine fuel control device based on stepper motor and pressure differential valve Figure 1The device is composed of a crude oil filter (1), a gear pump (2), a safety valve (3), a fine oil filter (4), a metering oil needle (5), a stepping motor (6), an angular displacement sensor (7), an aircraft engine controller (8), a pressure sensor (9), a speed sensor (10), an equal pressure difference valve (11), a main fuel cell valve (12), a starting fuel cell valve (13), a starting nozzle (14), a main fuel nozzle (15), a cleaning valve (16), a compressor rear air duct (17), etc.The crude oil filter (1) is connected to the gear pump (2) and is used to filter impurities in the fuel; the gear pump (2) is connected between the crude oil filter (1) and the fine oil filter (4) and is used to increase the fuel pressure; the safety valve (3) is connected to the inlet and outlet of the gear pump (2) and is used for fuel reflux; the fine oil filter (4) is connected between the gear pump (2) and the metering needle (5) and is used to further filter impurities in the fuel; the metering needle (5) is connected between the fine oil filter (4) and the main fuel cell valve (12) and is used for fuel flow metering; the stepping motor (6) is connected between the metering needle (5) and the aircraft engine controller (8) and receives the aircraft engine control signal. The pulse signal sent by the aircraft engine controller (8) pushes the metering oil needle (5) to the desired position; the angular displacement sensor (7) is connected between the metering oil needle (5) and the aircraft engine controller (8) to measure the angular displacement of the metering oil needle (5) and transmit the RVDT angular displacement signal to the aircraft engine controller (8); the aircraft engine controller (8) is connected to the stepper motor (6), the angular displacement sensor (7), the pressure sensor (9) and the speed sensor (10) to receive the RVDT angular displacement, pressure and speed signals and control the action of the stepper motor (6) through the pulse signal; the pressure sensor (9) is connected to the aircraft engine The invention relates to a fuel injection nozzle (11) and a fuel injection nozzle (12) connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector (5) and the fuel injector (14) into the fuel injection nozzle (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector (5) and the fuel injector (14) for injecting fuel from the fuel injector (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector (14) and the fuel injector (14) for injecting fuel from the fuel injector (14). Between the metering oil needle (5) and the starting nozzle (14), it is used to open and close the starting fuel valve; the starting nozzle (14) is connected to the starting fuel battery valve (13) and is used to spray the starting fuel into the combustion chamber; the main fuel nozzle (15) is connected to the main fuel battery valve (12) and is used to spray the main fuel into the combustion chamber; the cleaning valve (16) is connected between the starting nozzle (14) and the compressor rear air duct (17) and is used to clean the fuel on the starting nozzle (14) by using the compressor rear air duct (17); the compressor rear air duct (17) is connected to the cleaning valve (16) and is used to provide an air source for the compressor rear air duct (17) to clean the starting nozzle (14).

[0017] High-precision fuel control devices such as Figure 2 The device is composed of an FPGA control module (1), a power amplifier module (2), a stepper motor (3), a reducer (4), a fuel metering valve (5), an angular displacement sensor (6), etc.

[0018] A high-precision fuel metering stepper motor control subdivision method, such as Figure 3 As shown, the following steps are included: 1) Start running the program; 2) Read in the stepper motor subdivision data; 3) Determine whether the motor is rotating forward or reverse. If it is rotating forward, determine the motor speed and proceed to the next step. If it is rotating reversely, the motor stops running. 4) Determine whether it is deceleration. If not, run at the deceleration given motor running speed. If yes, run at the acceleration given motor running speed. 5) Further determine whether the motor has reached the fixed position (i.e. the fuel metering valve).

[0019] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A high-precision fuel metering device for a turbojet engine controlled by a stepper motor, and a device and control method for preventing the coking of a starting nozzle, characterized in that include: The high-precision fuel metering device for a turbojet aircraft engine comprises a coarse oil filter (1), a gear pump (2), a safety valve (3), a fine oil filter (4), a metering oil needle (5), a stepping motor (6), an angular displacement sensor (7), an aircraft engine controller (8), a pressure sensor (9), a speed sensor (10), an equal pressure difference valve (11), a main fuel solenoid valve (12), a starting fuel solenoid valve (13), a starting nozzle (14) and a main fuel nozzle (15); The crude oil filter (1) is connected to the gear pump (2) and is used to filter impurities in the fuel; the gear pump (2) is connected between the crude oil filter (1) and the fine oil filter (4) and is used to increase the fuel pressure; the safety valve (3) is connected to the inlet and outlet of the gear pump (2) and is used for fuel reflux; the fine oil filter (4) is connected between the gear pump (2) and the metering needle (5) and is used to further filter impurities in the fuel; the metering needle (5) is connected between the fine oil filter (4) and the main fuel solenoid valve (12) and is used for fuel flow metering; the stepping motor (6) is connected between the metering needle (5) and the aircraft engine controller (8) and receives the aircraft engine control signal. The pulse signal sent by the aircraft engine controller (8) pushes the metering oil needle (5) to the desired position; the angular displacement sensor (7) is connected between the metering oil needle (5) and the aircraft engine controller (8) to measure the angular displacement of the metering oil needle (5) and transmit the RVDT angular displacement signal to the aircraft engine controller (8); the aircraft engine controller (8) is connected to the stepper motor (6), the angular displacement sensor (7), the pressure sensor (9) and the speed sensor (10) to receive the RVDT angular displacement, pressure and speed signals and control the action of the stepper motor (6) through the pulse signal; the pressure sensor (9) is connected to the aircraft engine The invention relates to a fuel injection nozzle (11) and a fuel injection nozzle (12) connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector (14) to the fuel injector control device (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector control device (15) and the fuel injector control device (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector control device (15) and the fuel injector control device (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector control device (15) and the fuel injector control device (15). The fuel injection nozzle (11) is connected to the fuel injection nozzle (13) for injecting fuel from the fuel injector control device (15) and the fuel injector control device (15). Between the metering oil needle (5) and the starting nozzle (14), it is used to open and close the starting fuel valve; the starting nozzle (14) is connected to the starting fuel solenoid valve (13) and is used to spray the starting fuel into the combustion chamber; the main fuel nozzle (15) is connected to the main fuel solenoid valve (12) and is used to spray the main fuel into the combustion chamber; the cleaning valve (16) is connected between the starting nozzle (14) and the compressor rear air duct (17) and is used to clean the fuel on the starting nozzle (14) by using the compressor rear air duct (17); the compressor rear air duct (17) is connected to the cleaning valve (16) and is used to provide an air source for the compressor rear air duct (17) to clean the starting nozzle (14).

2. The device for preventing starting nozzle from coking according to claim 1, wherein: The invention comprises a cleaning valve (16), a compressor rear air duct (17) and a starting fuel nozzle (15). After the aircraft engine is successfully started, the cleaning valve (16) is opened to introduce the compressor rear pressure to clean the surface of the starting fuel nozzle (15), thereby preventing the fuel remaining on the end surface of the starting nozzle from being coked at high temperature and clogging the starting nozzle (15).

3. The high-precision fuel metering control method for an aircraft engine according to claim 1, wherein: The turbine aircraft engine controller (8) uses the RVDT angular displacement signals fed back by the pressure sensor (9), the rotation speed sensor (10) and the angular displacement sensor (7) and subdivides the step length of the stepping motor through a control algorithm to implement a pulse control signal sent by the aircraft engine controller (8) to the stepping motor (6), thereby controlling the operation of the stepping motor and pushing the metering oil needle (5) to a desired position, thereby achieving high-precision measurement of the fuel flow of the aircraft engine.

Images