Engine and method for controlling rotating speed of turbocharging piston engine

Abstract

The invention provides an engine which comprises an air inflow control device arranged at an air inlet of the engine and used for achieving accurate control over the air inflow. Meanwhile, the invention further provides a method for controlling the rotating speed of the turbocharged piston engine, and the method comprises the steps that 1, the required power of the helicopter is calculated according to the total pitch of the helicopter, the air speed and the atmospheric environment; 2, according to the required power of the helicopter, the air inflow and the oil injection quantity of an engine are controlled in advance, and constant-speed control over the rotating speed of helicopter rotors is achieved; the air inflow control device is additionally arranged at the air inlet of the engine, excessive air inflow is generated through turbocharging, then the air inflow control device is used for measuring the air inflow pressure through a sensor, precise control over the air inflow is achieved by bypassing a part of air inflow, it is ensured that the fluctuation of the rotating speed of the helicopter is small, the combustion efficiency is improved, and gasoline consumption is reduced.

Description

Technical Field

[0001] The present application belongs to the field of engine technology, and specifically relates to an engine and a method for controlling the speed of a turbocharged piston engine. Background Art

[0002] Generally speaking, constant speed control is rarely used in aviation gasoline piston engines at home and abroad. Even if constant speed control is used, the engine's self-closed loop constant speed control is currently generally used, which has poor control accuracy and cannot respond to the helicopter's rapidly changing power requirements in a timely manner. Summary of the Invention

[0003] Purpose of the invention: The present invention adopts collective pitch-load control, and gives the initial power extraction requirement of the engine according to the collective pitch power requirement under different atmospheric pressures and ambient temperatures of the helicopter. At the same time, the pre-boost pressure is set to a certain proportion of the actual demand (for example, 110% to 130%). The boost pressure is dynamic and needs to avoid the frequency doubling of the engine or helicopter speed.

[0004] In a first aspect, the present application provides an engine, comprising:

[0005] The air intake control device is arranged at the air intake of the engine, and is used to achieve precise control of the air intake volume.

[0006] Preferably, the engine further comprises:

[0007] The exhaust gas turbocharger is connected to the intake air control device, and the exhaust gas turbocharger is driven by the exhaust gas of the engine.

[0008] Preferably, the air intake control device includes:

[0009] A pressure sensor is provided at the engine air intake, and is used to measure the intake pressure;

[0010] a bypass connected to an air intake line of the engine;

[0011] Among them, if the exhaust gas turbocharger generates excessive intake air, the pressure sensor is used to measure the intake pressure, and a part of the intake air is bypassed through the bypass to achieve precise control of the intake air volume, ensuring that the helicopter speed fluctuation is small.

[0012] Preferably, the pressure sensor comprises:

[0013] a first pressure sensor, for measuring the pressure of the supercharged intake air;

[0014] The second pressure sensor is used to measure the pressure of the gas entering the engine.

[0015] Preferably, the engine further comprises:

[0016] The fuel injection actuator is used to control the fuel injection amount according to the engine intake volume.

[0017] In a second aspect, the present application further provides a method for controlling the speed of a turbocharged piston engine, the method comprising:

[0018] Step 1: Calculate the required power of the helicopter based on the helicopter's total distance, airspeed, and atmospheric conditions;

[0019] Step 2: According to the required power of the helicopter, the engine air intake and fuel injection amount are controlled in advance to achieve constant speed control of the helicopter rotor speed.

[0020] Preferably, the method further comprises:

[0021] Obtaining the helicopter's collective range based on the helicopter's design technical parameters;

[0022] The correspondence table between the helicopter collective pitch and the required helicopter power is obtained based on the calculated data or test data of the selected airfoil and the number of blades.

[0023] Preferably, the step 2 specifically includes:

[0024] The required power of the helicopter is converted into engine output power, and the intake air volume and fuel injection volume required for the engine to output this power are obtained based on the engine bench test results and atmospheric environment data.

[0025] By controlling the air intake and fuel injection amounts in advance, the engine output speed can be roughly adjusted to avoid excessive fluctuations in the engine output speed. Then, according to the deviation between the engine output speed and the set value, the air intake and fuel injection amounts are slightly adjusted to make the engine output speed constant, thereby achieving constant speed control of the helicopter rotor speed.

[0026] This application has the following technical effects:

[0027] The present invention adds an air intake control device at the engine air intake, generates excess air intake through turbocharging, and then uses the air intake control device to measure the air intake pressure through a sensor. By bypassing a part of the intake air, the air intake volume is precisely controlled, ensuring that the helicopter speed fluctuation is small, the combustion efficiency is improved, and gasoline consumption is saved. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a typical graph of total distance and required power during hovering;

[0029] Figure 2 This is a typical graph of total distance and required power during forward flight at a certain speed;

[0030] Figure 3This is a typical engine throttle and output power correspondence diagram;

[0031] Figure 4 This is a typical engine turbocharger control schematic;

[0032] Figure 5 It is a schematic diagram of the engine intake control device. DETAILED DESCRIPTION

[0033] It should be noted that the amount of fuel injected into the engine can be precisely controlled through sensors and actuators. The amount of air intake is affected by turbocharging control. The turbine uses the energy of hot exhaust gas to drive the compressor wheel, compressing the inhaled ambient air and then entering the cylinder through the carburetor.

[0034] The turbine's speed is primarily determined by the exhaust gas pressure acting on the turbine wheel, rather than directly by the engine speed. Exhaust gas pressure is affected by the engine's current power and speed, and intake air volume control is achieved through exhaust gas bypass. Because exhaust gas pressure is affected by engine speed and power, and exhaust gas bypass is difficult to precisely control and exhibits a certain degree of lag, precise intake air volume control is difficult to achieve.

[0035] The present invention adds an air flow control device to the engine's air intake, generating excess air flow through turbocharging. The air flow control device then uses a sensor to measure the intake pressure and, by bypassing a portion of the intake air, achieves precise air flow control. Furthermore, generating excess air flow through turbocharging allows the turbocharger's operating speed to avoid multiples of the engine or rotor speed, thus preventing harmful vibration excitation.

[0036] See also Figure 1-Figure 5 The present application provides a method for controlling the speed of a turbocharged piston engine, comprising the following steps:

[0037] Step 1: Calculate the required power of the helicopter based on the helicopter's total distance, airspeed, and atmospheric conditions;

[0038] Among them, the helicopter's collective pitch range is obtained according to the helicopter design technical parameters, and the helicopter's collective pitch and helicopter required power correspondence table is obtained according to the selected airfoil and blade number calculation data or test data. The correspondence between the collective pitch and power in a typical standard atmospheric environment is as follows: Figure 1 and Figure 2 shown.

[0039] The engine controller communicates with the helicopter to obtain the current collective distance and airspeed data of the helicopter. It then determines the required power of the helicopter under standard atmospheric conditions by looking up the table. It then measures the current atmospheric pressure and temperature based on its own sensors, corrects it based on the current atmospheric environment, and calculates the required power of the helicopter.

[0040] Step 2: According to the required power of the helicopter, the engine air intake and fuel injection amount are controlled in advance to achieve constant speed control of the helicopter rotor speed.

[0041] The helicopter's required power is converted into engine output power, which is then corrected based on engine bench test results and atmospheric environmental data to determine the air intake and fuel injection rates required for the engine to output this power. By controlling the air intake and fuel injection rates in advance, the engine's output speed can be roughly adjusted to prevent excessive fluctuations in the engine's output speed. Based on the deviation between the engine's output speed and the set value, the air intake and fuel injection rates are then fine-tuned to maintain constant engine output speed, thereby achieving constant helicopter rotor speed control.

[0042] The amount of fuel injected can be precisely controlled by sensors and actuators. The amount of air intake is affected by turbocharging control. The turbine uses the energy of hot exhaust gas to drive the compression wheel, compressing the inhaled ambient air and then entering the cylinder through the carburetor.

[0043] The turbine's speed is primarily determined by the exhaust gas pressure acting on the turbine wheel, rather than directly by the engine speed. Exhaust gas pressure is affected by the engine's current power and speed, and intake air volume control is achieved through exhaust gas bypass. Because exhaust gas pressure is affected by engine speed and power, and exhaust gas bypass is difficult to precisely control and exhibits a certain degree of lag, precise intake air volume control is difficult to achieve.

[0044] The present invention adds an air intake control device at the engine air intake, generates excess air intake through turbocharging, and then uses the air intake control device to measure the air intake pressure through a sensor. By bypassing a part of the intake air, the air intake volume is precisely controlled, ensuring that the helicopter speed fluctuation is small, the combustion efficiency is improved, and gasoline consumption is saved.

[0045] In other embodiments of the present application, the present application provides an engine, which includes: an intake volume control device, which is arranged at the engine air intake, and the intake volume control device is used to achieve precise control of the intake volume.

[0046] At the same time, the present application also provides a method for controlling the speed of a turbocharged piston engine, the method comprising: step 1, calculating the required power of the helicopter based on the helicopter's total distance, airspeed and atmospheric environment; step 2, controlling the engine's air intake and fuel injection amount in advance based on the required power of the helicopter to achieve constant speed control of the helicopter rotor speed.

[0047] The present invention adds an air intake control device at the engine air intake, generates excess air intake through turbocharging, and then uses the air intake control device to measure the air intake pressure through a sensor. By bypassing a part of the intake air, the air intake volume is precisely controlled, ensuring that the helicopter speed fluctuation is small, the combustion efficiency is improved, and gasoline consumption is saved.

[0048] The present invention adopts collective pitch-load control, and gives the engine initial power extraction requirement according to the collective pitch power requirement under different atmospheric pressures and ambient temperatures of the helicopter. At the same time, the pre-boost pressure is set to a certain proportion of the actual demand (for example, 110% to 130%). The boost pressure is dynamic and needs to avoid the frequency doubling of the engine or helicopter speed.

Claims

1. An engine, characterized in that: The engine comprises: The air intake control device is arranged at the air intake of the engine, and is used to achieve precise control of the air intake volume.

2. The engine according to claim 1, characterized in that The engine further comprises: The exhaust gas turbocharger is connected to the intake air control device, and the exhaust gas turbocharger is driven by the exhaust gas of the engine.

3. The engine according to claim 2, characterized in that The air intake control device comprises: A pressure sensor is provided at the engine air intake, and is used to measure the intake pressure; a bypass connected to an air intake line of the engine; Among them, if the exhaust gas turbocharger generates excessive intake air, the pressure sensor is used to measure the intake pressure, and a part of the intake air is bypassed through the bypass to achieve precise control of the intake air volume, ensuring that the helicopter speed fluctuation is small.

4. The engine according to claim 3, characterized in that The pressure sensor comprises: a first pressure sensor, for measuring the pressure of the supercharged intake air; The second pressure sensor is used to measure the pressure of the gas entering the engine.

5. The engine according to claim 1, characterized in that The engine further comprises: The fuel injection actuator is used to control the fuel injection amount according to the engine intake volume.

6. A method for controlling the speed of a turbocharged piston engine, characterized in that: The method comprises: Step 1: Calculate the required power of the helicopter based on the helicopter's total distance, airspeed, and atmospheric conditions; Step 2: According to the required power of the helicopter, the engine air intake and fuel injection amount are controlled in advance to achieve constant speed control of the helicopter rotor speed.

7. The method according to claim 6, characterized in that The method further comprises: Obtaining the helicopter's collective range based on the helicopter's design technical parameters; The correspondence table between the helicopter collective pitch and the required helicopter power is obtained based on the calculated data or test data of the selected airfoil and the number of blades.

8. The method according to claim 6, characterized in that The step 2 specifically includes: The required power of the helicopter is converted into engine output power, and the intake air volume and fuel injection volume required for the engine to output this power are obtained based on the engine bench test results and atmospheric environment data. By controlling the air intake and fuel injection amounts in advance, the engine output speed can be roughly adjusted to avoid excessive fluctuations in the engine output speed. Then, according to the deviation between the engine output speed and the set value, the air intake and fuel injection amounts are slightly adjusted to make the engine output speed constant, thereby achieving constant speed control of the helicopter rotor speed.

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