RU2774011C1 - Method for switching on the reversing device of a gas turbine engine when landing an aircraft - Google Patents

Abstract

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, in particular to methods for automatic control of gas turbine engines using thrust reverser. The method for turning on the reversing device of the gas turbine engine when landing the aircraft, which consists in the fact that the electronic regulator of the gas turbine engine regulates the thrust of the gas turbine engine and at the same time blocks the issuance of control signals to turn on the reversing device of the gas turbine engine when the aircraft is in the air; after the plane hits the runway, which is determined by the presence of the first information signal of the compression of the landing gear legs of the type "Two or three landing gear legs are compressed" or the second information signal "The landing gear is compressed" using the wheel speed sensor of the front landing gear of the aircraft, the engine control lever is moved to the minimum reverse thrust area, after that the information signal "Back thrust" is formed and the mechanical lock of the reversing device is opened, after opening the mechanical lock the information signal "Lock of the reversing device is not closed" is formed; however, after moving the engine control lever to the minimum reverse thrust area and the simultaneous presence of information signals “Two or three landing gear legs are crimped” or “Chassis is crimped”, “Back thrust”, “Reversing device lock is not closed” in automatic mode from the electronic engine controller issue a control action to transfer the reversing device from the “Forward thrust” position to the “Reverse thrust” position, the position of the reversing device is controlled (diagnosed) using a position sensor of the moving elements of the reversing device, an information signal to the cockpit “Reversing device is on” is formed, after transferring the reversing device to the “Reverse thrust” position, the engine control lever is moved to the position necessary to achieve the required reverse thrust value, and the engine operation mode is automatically set corresponding to the position of the engine control lever. Next, diagnostics of the aircraft rebound from the runway is carried out; traction, regardless of the presence of information signals "Two or three landing gear crimped" or "Chassis crimped".

EFFECT: present invention makes it possible to increase the reliability of turning on the reversing device of an aircraft engine when landing an aircraft with a rebound from the runway and to increase flight safety.

5 cl, 1 dwg

Description

The invention relates to the field of aircraft engine building, in particular to methods for automatic control of a gas turbine engine (GTE) using thrust reverser.

At present, almost all types of passenger and transport aircraft equipped with gas turbine engines use reverse devices that, at the command of the crew, using control systems, change the direction of the engine jet stream to the opposite, thereby creating engine reverse thrust and braking the aircraft during landing.

A known method of turning on the reversing device of a turbojet bypass engine, which consists in the fact that after touching the landing gear of the aircraft runway, which is determined by the simultaneous presence of information signals "Left landing gear crimped" and "Right landing gear crimped", move the engine control lever ( Throttle) to the “Small gas” platform, then the reverse control lever (RUR), pivotally connected to the throttle, is transferred to the “Minimum reverse thrust” platform, which ensures that the first control action is issued to open the reverse mechanical lock, also with the help of the RUR through the mechanical system rods and levers issue a second control action to transfer the reversing device from the "Forward thrust" position to the "Reverse thrust" position. With the help of limit switches, the opening of the mechanical lock of the reversing device and the position of the moving elements of the reversing device are determined, after opening the mechanical lock, an information signal is generated to the cockpit "Reverse lock is open", after the reversing device is transferred from the "Forward thrust" position to the "Reverse thrust" position, the information signal to the cockpit “Reverse is on”, then the RUR is transferred to the “Maximum reverse thrust” position, which ensures an increase in the fuel consumption supplied to the combustion chamber and, consequently, the maximum reverse thrust of the gas turbine engine (“PS-90A aircraft engine” under edited by Inozemtsev A.A., ed. M.: Libra-K, 2007, pp. 101-112, pp. 183-197).

As a result of turning on the reversing device to the "Maximum reverse thrust" mode, the aircraft is vigorously decelerated. When the aircraft reaches a predetermined run speed, at which it is possible for reverse gas jets to enter the engine, the crew switches the RUR to the minimum reverse thrust position, then, as necessary, the reverse device is turned off and the engine is switched to idle (forward thrust) to taxi the aircraft to the parking lot .

The disadvantages of analog should include:

- the complexity of the hydromechanical control system of the reversing device; the use of a special thrust reverse control lever, as well as a mechanical system of rods and levers to control the reverse device, which can reduce the reliability of the reverse switch due to possible breakdowns, distortions or jamming of mechanical elements;

- the risk of late switching on or not turning on the engine reversing device when the aircraft is landing due to the need for the simultaneous presence of the information signals "Left landing gear crimped" and "Right landing gear crimped". Such a situation is possible, for example, when the aircraft lands with a roll (only on the left or right landing gear) and/or under conditions of minimum weight loading, which may cause failure or late operation of at least one of the two landing gear compression sensors. In turn, the late activation or non-engagement of the reversing device simultaneously with the late activation of the air brake system (spoilers) and / or landing gear brakes and in combination with adverse factors (unstabilized approach, short runway, the presence of precipitation on it and etc.) can cause the aircraft to overrun the runway and even destroy the aircraft.

The closest in design implementation to the claimed invention is a method for controlling the reversing device of an aircraft engine during aircraft braking according to the patent (RU No. 2719778, IPC F02K 1/76, publ. 23.04.2020). This method of switching on the reversing device of the aircraft engine consists in the fact that the electronic engine regulator regulates the thrust of the gas turbine engine and at the same time blocks the issuance of control signals to turn on the reversing device of the gas turbine engine when the aircraft is in the air (until the moment it touches the runway); after the aircraft touches the runway, which is determined by the presence of the first information signal of the compression of the landing gear of the type "Two or three landing gear is compressed" or the second information signal "The landing gear is compressed" using the wheel speed sensor of the front landing gear of the aircraft, the engine control lever is moved to the platform of minimum reverse thrust, then the information signal "Reverse thrust" is generated and the mechanical lock of the reversing device is opened, after the mechanical lock is opened, the information signal "The lock of the reversing device is not closed" is generated; however, after moving the engine control lever to the minimum reverse thrust area and the simultaneous presence of information signals "Two or three landing gear legs are crimped" or "Chassis is crimped", "Reverse thrust", "Reversing device lock is not closed", in automatic mode from the electronic regulator the engine gives a control action to transfer the reversing device from the "Forward thrust" position to the "Reverse thrust" position, control (diagnose) the position of the reversing device using the position sensor of the moving elements of the reversing device, form an information signal to the cockpit "Reversing device is on" after the transfer reversing device to the “Reverse thrust” position, move the engine control lever to the position necessary to achieve the required reverse thrust value, then, as necessary, turn off the reversing device.

This method of turning on the reversing device contains the following drawback. In the event of a landing approach exceeding the landing horizontal/vertical speed, for example, due to pilot error or a sharp change in wind speed and direction along the landing course; after a short touch of the aircraft, it may bounce (separate) from the runway. As a result, after a short passage of the first and second information signals characterizing the compression of the landing gear, it is possible to remove them and, as a result, automatically block the activation of the reversing device in a situation where the pilot, taking into account the characteristics of the flight situation, needs to vigorously decelerate the aircraft by turning on the thrust reverser.

Blocking the activation of the reversing device can lead to the aircraft rolling out of the runway and to the destruction of the aircraft. An aircraft crash can also occur with excessive overloads that occur during the progressive goat of the aircraft, which is characterized by an increase in the amplitude of jumps (up to 3 ... 7 meters or more).

The technical problem, the solution of which is provided only by the implementation of the proposed invention and cannot be implemented using the prototype, is the insufficient reliability of turning on the reversing device of the aircraft engine when landing the aircraft with a rebound from the runway and insufficient flight safety in general.

The technical objective of the invention is to increase the reliability of turning on the reversing device of an aircraft engine when landing an aircraft with a rebound from the runway and to increase flight safety.

This is possible due to the short-term release of the blocking of the inclusion of the reversing device in various versions.

The technical problem is solved by the fact that in the method of turning on the reversing device of the gas turbine engine when the aircraft is landing, which consists in the fact that the electronic regulator of the gas turbine engine regulates the thrust of the gas turbine engine and at the same time blocks the issuance of control signals to turn on the reversing device of the gas turbine engine when the aircraft is in the air (until the moment of touching runway); after the aircraft touches the runway, which is determined by the presence of the first information signal of the compression of the landing gear of the type "Two or three landing gear is compressed" or the second information signal "The landing gear is compressed" using the wheel speed sensor of the front landing gear of the aircraft, the engine control lever is moved to the platform of minimum reverse thrust, the mechanical lock of the reversing device is opened, after opening the mechanical lock, the information signal "The lock of the reversing device is not closed" is generated; at the same time, after the engine control lever is moved to the minimum reverse thrust area in automatic mode, a control action is issued from the electronic engine controller to transfer the reverser device from the “Forward thrust” position to the “Reverse thrust” position, the position of the reverser device is monitored (diagnosed) using a position sensor moving elements of the reversing device, form an information signal to the cockpit "Reverser is on" after the reversing device is switched to the "Reverse thrust" position, move the engine control lever to the position necessary to achieve the required reverse thrust value, and automatically set the engine operation mode corresponding to position of the engine control lever, according to the invention, diagnostics of the aircraft rebound from the runway is carried out, in case of detecting the rebound of the aircraft from the runway in the electronic engine controller, b locking the control action to turn on the reversing device, while turning on the reversing device is carried out after the engine control lever is moved to the minimum reverse thrust area, regardless of the presence of information signals "Two or three landing gear legs are crimped" or "Chassis are crimped".

In addition, according to the invention, the diagnosis of the rebound of the aircraft from the runway is carried out by the formation and removal of the information signals "Two or three landing gear is crimped" or "Chassis is crimped".

In addition, the restoration of the blocking of the control action to turn on the reversing device is carried out after the engine control lever is moved from the reverse thrust position to the direct thrust position.

In addition, the restoration of the blocking of control signals to turn on the reversing device is carried out for a predetermined time τ after diagnosing the rebound of the aircraft from the runway.

In addition, according to the invention, the parameter τ is 5...10 s.

This time τ is sufficient for the pilot to determine the fact that the aircraft touched the runway and the subsequent switching on (activation) of the reversing device of the gas turbine engine. On the other hand, this time τ cannot be unlimited, because it is possible for the aircraft to go to the second circle and even go to the alternate airfield; in both such situations, the blocking of the reversing device in the air must be restored and ensured.

In FIG. 1 shows an enlarged block diagram of the implementation of the proposed method.

Block 1 of sensors-signals of compression of racks (supports) of the landing gear of the aircraft, sensor 2 of the speed of the wheel of the front landing gear of the aircraft, throttle 3 and sensor 4 for measuring the angle of the position of the engine control lever, module 5 for generating the information signal "Back thrust", gas turbine engine 6, in which includes an electronic regulator 7 and a reversing device 8 containing a mechanical lock 9 of the reversing device, a signaling device 10 for opening the reversing device lock and a sensor 11 for the position of the reversing device flaps.

The block 1 of sensors-indicators of compression of the landing gear of the aircraft generates the first information signal, which is fed to the first input of the electronic controller 7 in the case of compression of the landing gear, i.e. after the plane has landed. The wheel speed sensor 2 of the front landing gear generates the second information signal, which is fed to the second input of the electronic controller 7 and also characterizes the landing of the front landing gear on the runway. The output signal of the sensor 4 of the position of the engine control lever and the output signal of the module 5 of the formation of the information signal "Reverse thrust" are also fed to the input of the electronic controller 7.

The method is implemented as follows. In flight, the jet thrust control (modes of operation) of the gas turbine engine 6 is provided by moving the engine control lever 3 to the required position. At the same time, the inclusion of the reversing device 8 in the air is blocked, since the mechanical lock 9 of the reversing device 8 is closed, and the electronic controller 7 of the engine 6 blocked the formation of a control action to turn on the reversing device 8 at the command of the pilot due to the absence of the first or second information signals, which indicates to keep the aircraft in the air. The inclusion of the reversing device 8 is also not performed, due to the location of the throttle 3 outside the zone of operation of the reversing device, for example, on the site of low gas or cruising mode.

During a normal landing of the aircraft (without rebound from the runway), the reversing device is switched on according to a well-known algorithm, detailed in the prototype, namely, by transferring throttle 3 to the minimum reverse thrust site and then immediately after landing, the formation of the first or second information signals characterizing compression of landing gear supports, generation of signals “Back thrust”, “Reverse device lock not closed” and issuance of the corresponding control action from the electronic regulator 7 to the reversing device 8.

When landing an aircraft with a rebound from the runway, the first and/or possibly the second information signals pass for a short time (depending on the speed of rotation of the front wheel). The receipt and removal of these signals is recorded in the cockpit and is also recorded by the electronic controller 7 of the engine 6, in which the aircraft bounce is diagnosed and the blocking of the reversing device is unlocked. In such a situation, after a rebound and in the case of transfer of the throttle 3 to the platform of minimum reverse thrust, the blocking will be released and the reversing device 8 will be switched on (shifting to the “Reverse thrust” position), regardless of the landing gear compression signals. As a result - the necessary braking of the aircraft.

At the end of the landing run, the pilot turns off the reversing device 8, sequentially moving the throttle 3 to the area of minimum reverse thrust and then to the low forward thrust throttle. As a result, the reversing device 8 is shifted to the forward thrust position and at the same time the blocking of the reverse is restored.

Restoring the blocking of control signals to turn on the reversing device 8 can be implemented according to another option - at the end of a predetermined time τ after diagnosing the rebound of the aircraft from the runway.

The implementation of the reverse control system can also be any known, for example, electronic-electromechanical, electronic-hydromechanical, electro-hydraulic or electro-pneumatic using an electronic digital device. In a preferred embodiment, the reverse control system may be electronic-electromechanical.

Any known devices, for example, limit switches of the AM800K type, strain gauges, inductive displacement sensors, alarm systems of the "WoW" type (weight-on-wheels - weight on wheels) can be used as signaling sensors for the compression of the landing gear of the aircraft 1.

Any known types of rotation speed sensors, including magnetoelectric, induction, electromagnetic, etc., can be used as the wheel speed sensor 2 of the front landing gear of the aircraft. measures are provided to eliminate false data from the front landing gear wheel speed sensor during the operation of the proposed method.

It is clear to specialists in the field of aircraft construction that the organization of the transmission of information (signals) from block 1 and sensor 2 to the electronic controller 7 of engine 6 can be carried out, for example, via digital communication channels via twisted pair or fiber optic communication lines, in serial or parallel code using any known interface that implements them. In this case, it is possible to use intermediate aircraft units that convert the output signals of unit 1 and sensor 2 into a digital code (not shown in the diagram).

As the sensor 4 for measuring the position angle of the throttle 3, known angular displacement sensors can be used, for example, sine-cosine rotary transformers of the DBSKT type, but it is preferable to use induction sensors of the RVDT - Rotary Variable Differential Transformer type. The connection of the RVDT sensors with the throttle is mechanical, therefore, each angular position of the throttle 3 corresponds to a certain value of the angle of rotation of the RVDT sensor. The sensors are located directly in the cockpit to control the jet thrust of the engines. Each angular position of the throttle 3 corresponds to a certain value of the engine thrust. The transfer of throttle 3 to the position of switching on the reversing device 8 is a necessary condition for turning on the thrust reverser and, in fact, a sign of the crew's intention to start braking the aircraft using the reversing device 8.

As an electronic controller 7 can be used, for example, the Russian electronic engine controller RED-14 developed by JSC "UEC-Star", RF, which is a specialized multiprocessor digital computer system operating in real time. Structurally, the electronic regulator RED-14 is made in the form of a monoblock of rectangular section, which is placed on the engine housing. In the electronic controller 7 of the RED-14 type, the angle of rotation of the throttle 3, the temperature and pressure parameters of the air at the inlet to the engine 6 are measured, as well as the measurement of intra-engine parameters, such as, for example, the rotational speed of the engine rotors, the angle of rotation of the compressor inlet guide vane, temperature gases behind the low-pressure turbine, etc. (not shown in Fig. 1). Also, RED-14 controls the input information (discrete) signals necessary for the correct automatic control of the engine. Based on the received input information, the electronic engine controller, in accordance with the embedded control programs, provides control of the fuel consumption supplied to the engine combustion chamber, regulation of the position of the compressor inlet guide vanes, turning on and off the air bypass valves, turning on and off the engine reversing device, etc., which ultimately provides the required level of jet thrust of the gas turbine engine 6.

As an electronic regulator 7, a Western electronic regulator of the FADEC type (Full Authority Digital Engine Control system) with a functional structure according to the type of patent RU No. 2556474 (IPK F02K1 / 76, publ. 07.10.2015) can be used.

It is clear to specialists in the field of automatic control using digital systems that in the case of using the algorithm for unlocking the time τ, based on the experience of operating this type of aircraft, and the constant τ can be quickly adjusted by changing the software of the electronic controller 7.

As a reversing device 8, it is preferable to use a lattice type reversing device. This design is quite common and is used, for example, in the PD-14 engine for the MS-21 aircraft, in the PS-90A engine for the Il-96-300 and Tu-204/214 aircraft, in the D-18T engine for the AN-124 aircraft "Ruslan", in the Rolls-Royce Trent 500 engine for the A340-500/600 aircraft, in the V2500 engine for the A320-100/200 aircraft, etc. But in a more general case, other designs of the reversing device can be used, for example, folding or bucket type, which may slightly change the actuators, but this does not apply to the essence of the invention.

As a mechanical lock 9, a lock according to the type of technical solution disclosed in patent RU No. 2669452 (IPC: F02K 1/76, F02K 1/766, publ. 11.10.2018) can be used.

As a position sensor 11 of the moving elements of the reversing device 8, any known linear displacement sensors of the retractable rod of the reversing device or another type can be used.

Thus, the proposed invention with the above distinctive features, together with known features, makes it possible to increase the reliability of turning on the reverse device of an aircraft engine when landing an aircraft with a rebound from the runway and increase flight safety.

Claims (5)

1. The method of turning on the reversing device of the gas turbine engine when the aircraft is landing, which consists in the fact that the electronic regulator of the gas turbine engine regulates the thrust of the gas turbine engine and at the same time blocks the issuance of control signals to turn on the reversing device of the gas turbine engine when the aircraft is in the air; after the aircraft touches the runway, which is determined by the presence of the first information signal of the compression of the landing gear of the type "Two or three landing gear is compressed" or the second information signal "The landing gear is compressed" using the wheel speed sensor of the front landing gear of the aircraft, move the engine control lever to the platform of minimum reverse thrust, then the information signal "Reverse thrust" is generated and the mechanical lock of the reversing device is opened, after the mechanical lock is opened, the information signal "The lock of the reversing device is not closed" is generated; however, after moving the engine control lever to the minimum reverse thrust area and the simultaneous presence of information signals “Two or three landing gear legs are crimped” or “Chassis is crimped”, “Back thrust”, “Reversing device lock is not closed” in automatic mode from the electronic engine controller issue a control action to transfer the reversing device from the "Forward thrust" position to the "Reverse thrust" position, control (diagnose) the position of the reversing device using a position sensor of the moving elements of the reversing device, form an information signal to the cockpit "Reversing device is on" after the reversing device is switched devices in the “Reverse thrust” position move the engine control lever to the position necessary to achieve the required reverse thrust value, and automatically set the engine operating mode corresponding to the position of the engine control lever, characterized in that they diagnose the rebound itself flight from the runway, in the event of an aircraft rebound from the runway in the electronic engine controller, the blocking of the control action to turn on the reversing device is briefly removed, while the reversing device is turned on after moving the engine control lever to the area of minimum reverse thrust, regardless of the presence information signals "Two or three landing gear legs crimped" or "Chassis crimped". 2. The method of switching on the reversing device of the gas turbine engine during the landing of the aircraft according to claim 1, characterized in that the diagnosis of the rebound of the aircraft from the runway is carried out by the formation and removal of the information signals "Two or three landing gear is crimped" or "Chassis is crimped". 3. The method of turning on the reversing device of the gas turbine engine during landing of the aircraft according to claim 1, characterized in that the restoration of the blocking of the control action from the electronic regulator to turn on the reversing device is carried out after the engine control lever is moved from the reverse thrust position to the forward thrust position. 4. The method of turning on the reversing device of the gas turbine engine during landing of the aircraft according to claim 1, characterized in that the restoration of the blocking of the control action from the electronic regulator to turn on the reversing device is carried out for a predetermined time τ after diagnosing the rebound of the aircraft from the runway. 5. The method of turning on the reversing device of the gas turbine engine during landing of the aircraft according to claim 4, characterized in that the parameter τ is 5 ... 10 s.

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