Engine starting system and method based on double-engine aircraft

Abstract

The invention belongs to the field of aviation machinery, and relates to an engine starting system and method based on a double-engine aircraft. Comprising a left engine, a right engine, a first air turbine starter, a second air turbine starter, a first one-way valve, a second one-way valve, a first throttling valve, a second throttling valve, a third one-way valve, a fourth unloading valve, a two-inlet and one-outlet electromagnetic valve, a one-inlet and two-outlet electromagnetic valve and a controller. On the basis of an original structure, through the improved design, the problem of an engine starting air source of a single-engine stop engine is solved, and a power system of an aircraft does not need to be greatly changed. The method can be used for airplane ground starting and air single-engine parking starting, because the system does not need a small engine and does not need to maintain the small engine in the using process, on the premise that the redundancy of the starting system is not reduced, the maintenance cost is shortened, the maintenance period is shortened, and the airplane attendance rate is increased.

Description

Technical Field

[0001] The invention belongs to the field of aviation machinery and relates to an engine mutual starting system and method based on a twin-engine aircraft. Background Art

[0002] Aircraft engines provide thrust for aircraft, ensuring safe flight in the air, and provide power supply for the aircraft's electrical system and air bleed for the environmental control system. They provide a continuous and reliable source of power for the aircraft, while providing a comfortable riding and driving environment for pilots and passengers. Since the fuel-gas mixture in the combustion chamber needs to reach a certain pressure and temperature value before it can be ignited when the aircraft engine is started, the aircraft engine (hereinafter referred to as the "big engine") requires external force to start. The engine starting system is responsible for assisting the aircraft engine's speed to a certain value to meet the ignition requirements in the combustion chamber, thereby assisting in the starting of the aircraft engine. The auxiliary power unit (hereinafter referred to as the "small engine") is the main component of the starting system and provides the initial power for engine starting.

[0003] There are three types of small engines. One is the motor type, which uses the motor to drive the main engine through the gear structure; the second type is the gas generator type, which can be regarded as a small engine, and also drives the main engine through the gear mechanical structure; the third type is the air generator type, which uses the gas turbine to produce high-pressure gas, drives the air turbine starter assembled with the main engine, and transmits power to the main engine rotor through the gearbox structure. Summary of the invention

[0004] Purpose of the Invention

[0005] Provides an engine starting system solution for twin-engine aircraft without the need for an auxiliary power unit, capable of completing ground and air starts of the aircraft, and providing bleed air for the environmental control system.

[0006] Technical Solution

[0007] An engine mutual starting system based on a twin-engine aircraft comprises a left engine 1, a right engine 2, a first air turbine starter 3, a second air turbine starter 4, a first one-way valve 5, a second one-way valve 6, a first throttle valve 7, a second throttle valve 8, a third one-way valve 9, a fourth unloading valve 10, a two-input and one-output solenoid valve 11, a one-input and two-output solenoid valve 12, and a controller 13; the left engine 1 is connected to the first one-way valve 5 and the throttle valve 7 in sequence, and then to the a end of the two-input and one-output solenoid valve 11; the right engine 2 is connected to the second one-way valve 6 and the second throttle valve 8 in sequence, and then to the a end of the two-input and one-output solenoid valve 11; the first air turbine starter 10 is connected to the first one-way valve 5 and the throttle valve 7 in sequence, and then to the a end of the two-input and one-output solenoid valve 11; the first air turbine starter 10 ... second throttle valve 8 in sequence, and then to the a end of After the wheel starter 3 is connected to the air path of the second air turbine starter 4, it enters the C end of the one-in-two-outlet solenoid valve 12, the C end of the two-in-one-outlet solenoid valve 11 is connected to the a end of the one-in-two-outlet solenoid valve 12, the b end of the one-in-two-outlet solenoid valve 12 is connected to the bleed air, the b end of the two-in-one-outlet solenoid valve 11 is connected to the fourth unloading valve 10, the fourth unloading valve 10 is connected to the third one-way valve 9, and the third one-way valve 9 is connected to the air source; the controller 13 controls the on and off of the first air turbine starter 3, the second air turbine starter 4, the fourth unloading valve 10, the two-in-one-outlet solenoid valve 11, and the one-in-two-outlet solenoid valve 12 respectively.

[0008] Furthermore, the engine starting system protection method includes three modes.

[0009] Furthermore, the three modes are specifically: ground air source starting, air starting, and environmentally controlled air bleed.

[0010] Furthermore, the ground air source start is specifically used for ground start of the aircraft. When the aircraft is on the ground, the controller 13 issues a command after receiving a ground signal to control the unloading valve 10 to be in an open state.

[0011] The ground gas source equipment interface is connected to the inlet of system A, and the high-pressure gas provided by the equipment passes through the one-way valve 9 and is discharged into the atmosphere through the exhaust port of the unloading valve 10.

[0012] When the controller receives the command to start the left engine, the controller 13 sends a signal to open the valve of the air turbine starter 3, close the unloading valve 10, and the high-pressure gas enters the air turbine starter 3 through the one-way valve 9, the unloading valve 10, the two-inlet and one-outlet solenoid valve 11, and the one-inlet and two-outlet solenoid valve 12, driving the left engine 1 to start.

[0013] After the left engine is started, the controller 13 controls the unloading valve 10 to open, and the high-pressure gas is discharged out of the system.

[0014] When the controller receives the instruction to start the right engine, the controller 13 sends a signal to open the valve of the air turbine starter 4, close the unloading valve 10, and the high-pressure gas enters the air turbine starter 4 through the one-way valve 9, the unloading valve 10, the two-inlet and one-outlet solenoid valve 11, and the one-inlet and two-outlet solenoid valve 12, driving the left engine 2 to start.

[0015] After the left and right engines are started, the unloading valve 10 is opened, the gas is discharged from the system, and the ground gas source equipment stops working and the A interface is disconnected.

[0016] Furthermore, the air start is specifically used for starting an aircraft in the air. When the right engine stops while the aircraft is flying in the air, after the start switch is pressed, the controller 13 sends a signal to control the two-input-one-output solenoid valve 11 and the one-input-two-output solenoid valve 12, respectively connecting the a end and the c end on them, and controls the valve of the air turbine starter 4 on the right engine 2 to open, and the high-pressure gas of the left engine is introduced into the air turbine starter 4, driving the belt to start the right engine 2.

[0017] When the left engine stops while the aircraft is flying in the air, after the start switch is pressed, the controller 13 sends a signal to control the two-input-one-output solenoid valve 11 and the one-input-two-output solenoid valve 12, respectively connecting the a end and the c end on them, and controls the valve of the air turbine starter 3 on the left engine 1 to open, and the high-pressure gas of the left engine is introduced into the air turbine starter 3, driving the left engine 1 to start;

[0018] Furthermore, the environmental control air bleed is specifically used to supply high-pressure air to the environmental control system. After the two engines are started normally, when the environmental control air bleed switch is turned on, the controller 13 controls the a-end and c-end of the two-input and one-output solenoid valve 11 to be turned on, and the a-end and b-end of the one-input and two-output solenoid valve 12 to be turned on and connected to the c-end, and the left and right dual-engine gases pass through the first single-way valve 5 or the second single-way valve 6, the first throttle valve 7 or the second throttle valve 88 and then merge, and enter the environmental control system from the c-end outlet through the two-input and one-output solenoid valve 11 and the one-input and two-output solenoid valve 12.

[0019] Furthermore, a twin-engine turbofan aircraft is provided with the engine interconnection system as described in claim 1.

[0020] Furthermore, the twin-engine turbofan aircraft is started using the mutual starting method as described in claim 2.

[0021] The beneficial effects of this application are:

[0022] 1. Low cost of use. Based on domestic and foreign aircraft research, an aircraft is equipped with 5 to 6 small engines during its life, and the cost of using small engines during an aircraft cycle, including repairs and renovations, is tens of millions; the present invention can complete the ground and air start of large engines without the need for small engines, thus significantly reducing the cost of the aircraft start system.

[0023] 2. Short maintenance cycle. The present invention can be used for ground starting of aircraft and single-engine parking starting in the air, because the system does not need a small engine and does not need to be maintained during use. Under the premise of not reducing the redundancy of the starting system, the maintenance cost and cycle are shortened, and the aircraft attendance rate is improved.

[0024] 3. Break through foreign restrictions. The small engine is essentially a small aircraft engine. The aircraft engine is known as the jewel in the crown of industry. Its complexity is self-evident. It has long been the shortcoming of my country's industry. In addition, foreign countries have technical restrictions on China's aviation industry. The small engine has few types of models, long research and development cycles, and "money can't buy" and other problems have hindered the development of the aviation industry. The present invention can replace the small engine to complete the starting function.

[0025] 4. Aircraft weight reduction. There are many types of aircraft and the reduced structures have many advantages. The reduced weight can be used for the installation needs of other equipment; for example, more passenger seats are provided for passenger aircraft, which can carry more passengers.

[0026] Aircraft weight reduction: Taking a small twin-engine turbofan aircraft as an example, the weight of the small engine and related accessories is between 60kg and 70kg, which can be reduced by 60kg to 70kg. The reduced weight can be used for the installation of other equipment, and the fuel economy is improved after the weight reduction.

[0027] 5. Application on the ground, when there is no air source, when there is no air source, the air source of one engine can be used to supply air to the other engine, so as to start the air source of a single engine that has stopped, without the need to reconnect to the ground air source, thus improving the ground maintainability of the aircraft.

[0028] 6. The aircraft structural design has not been changed, and other functions on board will not be affected. Based on the original structure, the air source problem of a single-engine shutdown engine has been solved through improved design.

[0029] The structural design of the aircraft is not changed and the invention is applicable to most twin-engine aircrafts. The invention solves the problem of the engine starting air source of a single-engine parking engine by improving the design based on the original structure, without making major changes to the aircraft power system.

[0030] 7. What are the hazards of a single engine stopping in the air? The design of the present invention solves the above problems and can better avoid crashes, economic losses, etc. (Hazards of single engine stopping in the air)

[0031] If a single engine stops in the air, at a low airspeed, only the small engine can be used to start the small engine. There are strict restrictions on starting the small engine in the air, and the altitude needs to be lowered to the small engine starting envelope, which increases the risk of emergency handling of the aircraft. The design of the present invention solves the above problem, and the single engine stop failure can be handled more quickly, avoiding the risk of the aircraft crashing due to missing the best handling time.

[0032] The present invention provides a system which can start a large engine on the ground and in the air without a small engine, and provides bleed air for an environmental control system, and is suitable for aircraft equipped with twin engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 Schematic diagram of the engine mutual start system flow based on a twin-engine aircraft;

[0034] The figure includes: left engine 1, right engine 2, air turbine starter 3, air turbine starter 4, one-way valve 5, one-way valve 6, throttle valve 7, throttle valve 8, one-way valve 9, unloading valve 10, two-inlet and one-outlet solenoid valve 11, one-inlet and two-outlet solenoid valve 12, and controller 13. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical scheme and advantages of the implementation of the present invention clearer, the technical scheme in the embodiment of the present invention will be described in more detail in combination with the embodiment of the present invention. In the example, the same or similar reference numerals throughout represent the same or similar originals or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, not all of them. The embodiments described below by reference are exemplary and intended to be used to explain the present invention, and should not be construed as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present invention. The following is a detailed description in combination with the embodiments of the present invention.

[0036] The invention relates to a power device starting and air bleed system based on a twin-engine aircraft, which is divided into three working modes: ground air source starting, air starting and environmental control air bleed.

[0037] Ground air source starting: The ground equipment provides an air source with a certain pressure and temperature. The gas is introduced into the left and right air turbine starters of the engine through the one-way valve, unloading valve, and solenoid valve in sequence. The air source drives the turbine starter to operate and drive the engine to start. There is no need for an air source stage during the starting process, and the air source is discharged from the system by the unloading valve.

[0038] After starting, the left and right engines draw air through the compressor, and then merge through the throttle valve and are controlled by the solenoid valve to provide air for the environmental control system.

[0039] Environmental control air bleed: When the left and right engines are working normally, high-temperature and high-pressure gas is drawn out from the engine compressor, combined after being limited by the one-way valve and throttle valve, and introduced into the environmental control system through the solenoid valve.

[0040] Starting in the air: When a single engine of an aircraft stops in the air and an in-air start is required, air is bleed from the compressor of the normally functioning engine, passed through the throttle valve, and then controlled by the right solenoid valve to be introduced into the turbine starter of the stopped engine, driving the turbine starter to start the stopped engine.

[0041] The air turbine starter 3 and the air turbine starter 4 are respectively installed on the left engine 1 and the right engine 2, and are connected to the engine mechanical gears; the one-way valve 5 and the one-way valve 6 are respectively connected to the left engine 1 and the right engine 2, and are connected to the engine air intake pipeline; the one-way valve 5, the one-way valve 6, the throttle valve 7, the throttle valve 8, the one-way valve 9, the unloading valve 10, the two-input and one-outlet solenoid valve 11, and the one-input and two-outlet solenoid valve 12 are pipeline-connected; the air turbine starter 3, the air turbine starter 4, the unloading valve 10, the two-input and one-outlet solenoid valve 11, and the one-input and two-outlet solenoid valve 12 are all electrically connected to the controller 13.

[0042] The present invention is divided into three working modes: ground air source starting, air starting and environmentally controlled air bleed.

[0043] Ground air start

[0044] Used for ground start of aircraft. When the aircraft is on the ground, the controller 13 issues a command after receiving a ground signal to control the unloading valve 10 to be in an open state.

[0045] The ground gas source equipment interface is connected to the inlet of system A, and the high-pressure gas provided by the equipment passes through the one-way valve 9 and is discharged into the atmosphere through the exhaust port of the unloading valve 10.

[0046] When the controller receives the command to start the left engine, the controller 13 sends a signal to open the valve of the air turbine starter 3, close the unloading valve 10, and the high-pressure gas enters the air turbine starter 3 through the one-way valve 9, the unloading valve 10, the two-inlet and one-outlet solenoid valve 11, and the one-inlet and two-outlet solenoid valve 12, driving the left engine 1 to start.

[0047] After the left engine is started, the controller 13 controls the unloading valve 10 to open, and the high-pressure gas is discharged out of the system.

[0048] When the controller receives the instruction to start the right engine, the controller 13 sends a signal to open the valve of the air turbine starter 4, close the unloading valve 10, and the high-pressure gas enters the air turbine starter 4 through the one-way valve 9, the unloading valve 10, the two-inlet and one-outlet solenoid valve 11, and the one-inlet and two-outlet solenoid valve 12, driving the left engine 2 to start.

[0049] After the left and right engines are started, the unloading valve 10 is opened, the gas is discharged from the system, and the ground gas source equipment stops working and the A interface is disconnected.

[0050] Environmental control air bleed

[0051] Used to supply high-pressure air to the environmental control system. After the double engines start normally, when the environmental control air bleed switch is turned on, the controller 13 controls the two-input and one-outlet solenoid valve 11 (a and c ends are connected) and the one-input and two-outlet solenoid valve 12 (a and b ends are connected) to connect with the C port, and the left and right double-engine gases pass through the one-way valve 5 / 6 and the throttle valve 7 / 8 and then merge, and enter the environmental control system from the C outlet through the two-input and one-outlet solenoid valve 11 and the one-input and two-outlet solenoid valve 12.

[0052] Air or ground start

[0053] Used for starting the aircraft in the air. When the right engine stops while the aircraft is flying in the air, after pressing the start switch, the controller 13 sends a signal to control the two-input and one-output solenoid valve 11 and the one-input and two-output solenoid valve 12, respectively connecting the a and c ends on them, and controlling the valve of the air turbine starter 4 on the right engine 2 to open, and the high-pressure gas of the left engine is introduced into the air turbine starter 4, driving the belt to start the right engine 2.

[0054] When the left engine stops while the aircraft is flying in the air, after the start switch is pressed, the controller 13 sends a signal to control the two-input and one-output solenoid valve 11 and the one-input and two-output solenoid valve 12, respectively connecting the a and c ends thereof, and controls the valve of the air turbine starter 3 on the left engine 1 to open, and the high-pressure gas of the left engine is introduced into the air turbine starter 3, driving the left engine 1 to start.

[0055] It is understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as the general understanding of ordinary technicians in the field to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and unless defined as here, will not be interpreted with idealized or overly formal meanings. The specific implementation methods described above further describe the purpose, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Within the spirit and principle of the present invention, any technician familiar with the profession may use the above disclosed technical content to change or modify it into an equivalent embodiment of equivalent changes for application in other fields, but any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution content of the present invention, any modification, equivalent replacement, improvement, etc., made according to the technical essence of the present invention, should be included in the protection scope of the present invention.

Claims

1. An engine mutual starting system based on a twin-engine aircraft, characterized in that: The invention comprises a left engine, a right engine, a first air turbine starter, a second air turbine starter, a first one-way valve, a second one-way valve, a first throttle valve, a second throttle valve, a third one-way valve, a fourth unloading valve, a two-input and one-output solenoid valve, a one-input and two-output solenoid valve, and a controller; the left engine is connected to the first one-way valve and the throttle valve in sequence, and then connected to the a end of the two-input and one-output solenoid valve, and the right engine is connected to the second one-way valve and the second throttle valve in sequence, and then connected to the a end of the two-input and one-output solenoid valve; the first air turbine starter and the second air turbine starter are connected to each other. After the air path of the air turbine starter is connected, it enters the C end of the one-inlet and two-outlet solenoid valve, the C end of the two-inlet and one-outlet solenoid valve is connected to the A end of the one-inlet and two-outlet solenoid valve, the B end of the one-inlet and two-outlet solenoid valve is connected to the bleed air, the B end of the two-inlet and one-outlet solenoid valve is connected to the fourth unloading valve, the fourth unloading valve is connected to the third one-way valve, and the third one-way valve is connected to the air source; the controller controls the on and off of the first air turbine starter, the second air turbine starter, the fourth unloading valve, the two-inlet and one-outlet solenoid valve, and the one-inlet and two-outlet solenoid valve respectively.

2. The method for mutual activation of systems as claimed in claim 1, characterized in that: Includes three modes.

3. The mutual activation method according to claim 2, characterized in that: The three modes are specifically: ground air source starting, air starting, and environmentally controlled air bleed.

4. The mutual activation method according to claim 3, characterized in that: The ground air source start is specifically used for ground start of the aircraft; when the aircraft is on the ground, the controller receives a ground signal and issues a command to control the unloading valve to be in an open state; The ground gas source equipment interface is connected to the inlet of system A. The high-pressure gas provided by the equipment passes through the one-way valve and is discharged into the atmosphere through the exhaust port of the unloading valve; When the controller receives the command to start the left engine, the controller sends a signal to open the valve of the air turbine starter and close the unloading valve. The high-pressure gas enters the air turbine starter through the one-way valve, the unloading valve, the two-in-one-out solenoid valve, and the one-in-two-out solenoid valve, and drives the left engine to start. After the left engine is started, the controller controls the unloading valve to open, and the high-pressure gas is discharged out of the system; When the controller receives the command to start the right engine, the controller sends a signal to open the valve of the air turbine starter and close the unloading valve. The high-pressure gas enters the air turbine starter through the one-way valve, the unloading valve, the two-in-one-out solenoid valve, and the one-in-two-out solenoid valve, and drives the left engine to start. After the left and right engines are started, the unloading valve opens, the gas is discharged from the system, and the A interface is disconnected after the ground gas source equipment stops working.

5. The mutual activation method according to claim 3, characterized in that: The air start is specifically used for starting an aircraft in the air; when the right engine stops while the aircraft is flying in the air, after pressing the start switch, the controller sends a signal to control the two-input-one-output solenoid valve and the one-input-two-output solenoid valve, respectively connecting the a end and the c end on them, and controls the air turbine starter valve on the right engine to open, and the high-pressure gas of the left engine is introduced into the air turbine starter, driving the right engine to start; When the aircraft is flying in the air, the left engine stops. When the start switch is pressed, the controller sends a signal to control the two-input and one-output solenoid valve and the one-input and two-output solenoid valve, respectively connecting the a end and c end on them, and controls the air turbine starter valve on the left engine to open, and the high-pressure gas of the left engine is introduced into the air turbine starter, driving the left engine to start.

6. The mutual activation method according to claim 3, characterized in that: The environmental control air bleed is specifically used to supply high-pressure air to the environmental control system. After the two engines are started normally, when the environmental control air bleed switch is turned on, the controller controls the a-end and c-end of the two-inlet and one-outlet solenoid valve to be connected, and the a-end and b-end of the one-inlet and two-outlet solenoid valve to be connected and connected with the c-end. The left and right double-engine gases pass through the first one-way valve or the second one-way valve, the first throttle valve or the second throttle valve, and then merge, and enter the environmental control system from the c-end outlet through the two-inlet and one-outlet solenoid valve and the one-inlet and two-outlet solenoid valve.

7. A twin-engine turbofan aircraft equipped with the engine mutual starting system according to claim 1.

8. A twin-engine turbofan aircraft, characterized in that: The mutual initiation method as claimed in claim 3 is adopted for initiation.

Images