A hybrid power system for aircraft and a control method thereof

Abstract

The present application belongs to the technical field of aircraft power system design, and specifically relates to an aircraft hybrid power system and a control method thereof, wherein the aircraft hybrid power system includes a main engine, a ducted fan, a starter generator, a cooling fan, a generator, and a lubricating oil pipeline; the main engine is arranged at the tail of the aircraft, and adopts a large bypass ratio turbofan engine, including a fan, a compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and a nozzle arranged in sequence; a starter generator and a cooling fan are arranged in the front cavity of the main engine, the starter generator is connected to the high-pressure shaft of the main engine, the cooling fan is connected to the low-pressure shaft of the main engine, the cooling fan is located in front of the starter generator, and the starter generator is connected to the main engine and its aircraft power system; a generator is arranged in the rear cavity of the main engine and a lubricating oil pipeline is inserted, and the generator is connected to the low-pressure shaft; there are two ducted fans, which are arranged under two wings, connected to the generator, and a hydrogen combustion chamber is provided.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft power system design, and specifically relates to an aircraft hybrid power system and a control method thereof. Background Art

[0002] High bypass ratio turbofan engines have the advantages of low fuel consumption and high thrust, and are an important choice for aircraft, especially transport aircraft.

[0003] At present, most aircraft engines use small gas turbines as starters. Under the conditions of thin air and low temperature in the plateau, the combustion conditions are poor and the starting time is long, making it difficult to start the engine. At the same time, due to the low engine intake pressure and small engine starting thrust, the aircraft has difficulty taking off and the taxiing distance is long, which limits the aircraft's ability to perform missions.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide an aircraft hybrid power system and a control method thereof to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] On the one hand, an aircraft hybrid power system is provided, including a main engine, a ducted fan, a starter generator, a cooling fan, a generator, and a lubricating oil pipeline;

[0008] The main engine is installed at the tail of the aircraft and adopts a high bypass ratio turbofan engine, including a fan, a compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and a nozzle arranged in sequence;

[0009] A starter generator and a cooling fan are arranged in the front cavity of the main engine. The starter generator is connected to the high-pressure shaft of the main engine, and the cooling fan is connected to the low-pressure shaft of the main engine. The cooling fan is located in front of the starter generator, and the starter generator is connected to the main engine and the power system of the aircraft;

[0010] A generator is arranged in the rear cavity of the main engine and a lubricating oil pipeline is inserted, and the generator is connected to the low-pressure shaft;

[0011] There are two ducted fans, installed under the two wings, connected to generators, and equipped with hydrogen combustion chambers.

[0012] Optionally, the above aircraft hybrid power system further includes an integrated energy management system;

[0013] The integrated energy management system is set outside the main engine;

[0014] The generator is connected to the integrated energy management system;

[0015] The generator is connected to an integrated energy management system.

[0016] Optionally, in the above aircraft hybrid power system, the ducted fan includes an outer casing, a guide cone, an electric fan, a rectifier support plate, a hydrogen injection rod, an ignition nozzle, and an electric motor;

[0017] The guide cone is arranged inside the outer casing and has an annular gap at the front end;

[0018] The electric fan is arranged in the outer casing, in the annular gap;

[0019] There are multiple rectifying support plates, which are supported between the outer casing and the guide cone along the circumferential direction and are located behind the electric fan to form a hydrogen combustion chamber between the outer casing and the guide cone;

[0020] There are multiple hydrogen injection rods, which are arranged through the outer casing and extend into each rectifying support plate, and the injection nozzles extend from the two side walls of the rectifying support plate;

[0021] The ignition nozzle is arranged through the outer casing and extends into the hydrogen combustion chamber;

[0022] The electric motor is arranged in the guide cone, connected to the generator through a line, and its rotating shaft is connected to the electric fan.

[0023] Optionally, in the above aircraft hybrid power system, the ducted fan further includes an annular pipe, a high-pressure hydrogen storage tank, and a one-way opening and closing valve;

[0024] The annular pipe sleeve is arranged on the outer periphery of the outer casing, connects each hydrogen injection rod, and is connected to the high-pressure hydrogen storage tank through a pipeline, and a one-way opening and closing valve is arranged on the pipeline connected to the high-pressure hydrogen storage tank.

[0025] On the other hand, a method for controlling an aircraft hybrid power system is provided, for controlling the aircraft hybrid power system, comprising:

[0026] When starting the main engine, the integrated energy management system drives the starter generator to drive the high-pressure shaft to rotate until the combustion chamber is successfully ignited and the main engine is started. After the main engine is successfully started, the starter generator is converted to power generation mode to supply power to the main engine and its aircraft.

[0027] When the aircraft takes off, the integrated energy management system controls the generator to output power to the ducted fan, driving the ducted fan to operate at low power;

[0028] When the aircraft is cruising, the integrated energy management system controls the generator to increase the power output to the ducted fan, driving the ducted fan to operate at high power;

[0029] When the aircraft requires greater thrust, the hydrogen combustion chamber that controls the ducted fan operates.

[0030] This application has at least the following beneficial technical effects:

[0031] Provided are an aircraft hybrid power system and a control method thereof, wherein a starter-generator is used to start a main engine, which is less affected by environmental conditions such as air pressure and temperature, and can realize reliable starting of the main engine. A ducted fan is driven by a generator through a low-pressure shaft of the main engine, thereby further improving the bypass ratio, increasing the intake flow rate, and increasing the thrust. In addition, the ducted fan is provided with a hydrogen combustion chamber, and the characteristics of hydrogen combustion speed and high flame temperature can be utilized to greatly increase the exhaust temperature and speed of the ducted fan, thereby further increasing the thrust of the power system, meeting the requirements for aircraft take-off under harsh conditions such as plateaus, and improving the aircraft's ability to perform missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 is a schematic diagram of an aircraft hybrid power system provided by an embodiment of the present application;

[0033] Figure 2 It is a schematic diagram of a main engine, an integrated energy management system, a starter generator, a cooling fan, a generator, and a lubricating oil pipeline provided in an embodiment of the present application;

[0034] Figure 3 is a schematic diagram of a ducted fan provided in an embodiment of the present application;

[0035] in:

[0036] 1-main engine; 2-ducted fan; 3-integrated energy management system; 4-generator; 5-cooling fan; 6-generator; 7-lubricating oil pipeline;

[0037] 11-fan; 12-compressor; 13-combustion chamber; 14-high-pressure turbine; 15-low-pressure turbine; 16-nozzle; 17-high-pressure shaft; 18-low-pressure shaft;

[0038] 21-outer casing; 22-guide cone; 23-electric fan; 24-rectifier support plate; 25-hydrogen injection rod; 26-annular pipe; 27-high-pressure hydrogen storage tank; 28-one-way opening and closing valve; 29-ignition nozzle; 210-electric motor.

[0039] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0040] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0041] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0042] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0043] An aircraft hybrid power system, such as Figure 1 As shown, it includes a main engine 1, a ducted fan 2, an integrated energy management system 3, a starter generator 4, a cooling fan 5, a generator 6, and a lubricating oil pipeline 7.

[0044] The main engine 1 is arranged at the tail of the aircraft and adopts a high bypass ratio turbofan engine, including a fan 11, a compressor 12, a combustion chamber 13, a high-pressure turbine 14, a low-pressure turbine 15, and a nozzle 16 arranged in sequence. Figure 2 shown.

[0045] The integrated energy management system 3 is provided outside the main engine 1 .

[0046] A generator 4 and a cooling fan 5 are arranged in the front cavity of the main engine 1. The generator 4 is connected to the high-pressure shaft 17 of the main engine 1, and the cooling fan 5 is connected to the low-pressure shaft 18 of the main engine 1. The cooling fan 5 is located in front of the generator 4. Figure 2 As shown, the generator 4 is connected to the integrated energy management system 3, and is connected to the main engine 1 and the electrical system of the aircraft.

[0047] A generator 6 is arranged in the rear cavity of the main engine 1 and a lubricating oil pipeline 7 is inserted therein. The generator 6 is connected to a low-pressure shaft 18 and to an integrated energy management system 3, such as Figure 2 shown.

[0048] There are two ducted fans 2, which are arranged under the two wings, connected to the generator 6, and provided with a hydrogen combustion chamber.

[0049] In the aircraft hybrid power system disclosed in the above embodiment, the integrated energy management system 3 can drive the starter generator 4 to drive the high-pressure shaft 17 to rotate until the combustion chamber 13 is successfully injected and ignited, so that the main engine 1 is started. After the main engine 1 is successfully started, the starter generator 4 can be converted into a power generation mode to supply power to the main engine 1 and its aircraft. During this process, the cooling fan 5 will rotate driven by the low-pressure shaft 18 to blow air to cool the starter generator 4.

[0050] In the aircraft hybrid power system disclosed in the above embodiment, a ducted fan 2 is provided in conjunction with the main engine 1, which can increase the equivalent bypass ratio of the power system, reduce fuel consumption, and meet the needs of long-term flight of the aircraft. However, the existence of the ducted fan 2 itself will increase the frontal area of ​​the power system and increase the frontal resistance of the power system. For this reason, when the aircraft takes off, the integrated energy management system 3 can control the generator 6 to output a small amount of power to the ducted fan 2, that is, extract a small amount of power from the main engine 1, and the power can meet the minimum power of the ducted fan 2 to drive the ducted fan 2 to operate at a low power to achieve flow resistance reduction. Most of the thrust required for the aircraft to take off is generated by the main engine 1; when the aircraft is cruising, the integrated energy management system 3 can control the generator 6 to increase the power output to the ducted fan 2, that is, increase the extraction of the power of the main engine 1, drive the ducted fan 2 to operate at a high power, and make the ducted fan 2 generate more thrust to reduce the fuel consumption rate. In addition, when the generator 6 is working, lubricating oil can be introduced through the lubricating oil pipeline 7 to cool the generator 6.

[0051] The aircraft hybrid power system disclosed in the above embodiment, when the aircraft needs greater thrust, for example, when taking off under harsh conditions such as plateaus, and the thrust demand cannot be met by adjusting the operation of the main engine 1 and the ducted fan 2, the hydrogen combustion chamber of the ducted fan 2 is controlled to operate. Hydrogen has the characteristics of rapid combustion and high flame temperature, which can rapidly increase the exhaust temperature and speed of the ducted fan 2 in a short time, greatly increasing the thrust of the ducted fan 2, thereby achieving a short-term thrust increase of the power system and ensuring the take-off of the aircraft.

[0052] The aircraft hybrid power system disclosed in the above-mentioned embodiment uses a starter generator 4 to start the main engine 1, which is less affected by environmental conditions such as air pressure and temperature, and can achieve reliable starting of the main engine 1, and drives the ducted fan 2 with the generator 6 through the low-pressure shaft 18 of the main engine 1, thereby further improving the bypass ratio, increasing the intake flow rate, and increasing the thrust. In addition, the ducted fan 2 is provided with a hydrogen combustion chamber, which can utilize the characteristics of hydrogen's fast combustion speed and high flame temperature to greatly increase the exhaust temperature and speed of the ducted fan 2, further increase the thrust of the power system, meet the needs of the aircraft taking off in harsh conditions such as plateaus, and improve the aircraft's ability to perform missions.

[0053] Ducted fan 2 Figure 3 As shown, it includes an outer casing 21, a guide cone 22, an electric fan 23, a rectifying support plate 24, a hydrogen injection rod 25, an annular pipe 26, a high-pressure hydrogen storage tank 27, a one-way opening and closing valve 28, an ignition nozzle 29, and a motor 210.

[0054] The guide cone 22 is arranged in the outer casing 21 and has an annular gap at the front end.

[0055] The electric fan 23 is arranged in the outer casing 21 and is located in the annular gap.

[0056] There are a plurality of rectifying support plates 24 , which are supported between the outer casing 21 and the guide cone 22 along the circumferential direction and are located behind the electric fan 23 , forming a hydrogen combustion chamber between the outer casing 21 and the guide cone 22 .

[0057] There are multiple hydrogen injection rods 25 that penetrate the outer casing 21 and extend into each rectifying support plate 24 , and the injection nozzles thereof extend from the two side walls of the rectifying support plate 24 .

[0058] The annular tube 26 is sleeved on the outer periphery of the outer casing 21 , connected to each hydrogen injection rod 25 , and connected to the high-pressure hydrogen storage tank 27 through a pipeline, and a one-way opening and closing valve 28 is provided on the pipeline connected to the high-pressure hydrogen storage tank 27 .

[0059] The ignition nozzle 29 is disposed through the outer casing 21 and extends into the hydrogen combustion chamber.

[0060] The electric motor 210 is disposed in the guide cone 22 , connected to the generator 6 via a line, and its rotating shaft is connected to the electric fan 23 .

[0061] When the ducted fan 2 needs to be operated, the integrated energy management system 3 controls the generator 6 to output power to the motor 210, extracts the power of the main engine 1, drives the motor 210 to work, and drives the electric fan 23 of the ducted fan 2 to operate and generate thrust.

[0062] When the hydrogen combustion chamber of the ducted fan 2 needs to work, the one-way on-off valve 28 is controlled to open, so that the hydrogen in the high-pressure hydrogen storage tank 27 enters each hydrogen injection rod 25 through the annular tube 26, and is then sprayed into the hydrogen combustion chamber by the injection nozzle on the hydrogen injection rod 25, and ignited and burned by the ignition nozzle 29, thereby increasing the temperature and speed of the exhaust gas of the ducted fan 2 and increasing the thrust of the ducted fan 2.

[0063] The hydrogen required for the operation of the hydrogen combustion chamber of the ducted fan 2 is supplied by a high-pressure hydrogen storage tank 27 and controlled by a one-way opening and closing valve 28. No complex mechanism such as a hydrogen flow monitoring valve is provided to reduce the difficulty of hydrogen transmission. The hydrogen injection is only supplied by a single gas line, which can reduce the complexity of the pipeline and improve the reliability and safety of hydrogen use. The hydrogen combustion chamber is only used under plateau conditions and a small amount of conditions that require greater thrust. The outlet temperature of the hydrogen combustion chamber is controlled below 800K to avoid high temperature damage.

[0064] During takeoff and flight of the aircraft, the energy management system 3 determines the power output by the main engine 1 to the ducted fan 2 and whether the hydrogen combustion chamber is working.

[0065] A method for controlling a hybrid power system of an aircraft is provided, which is used to control the hybrid power system of the aircraft disclosed in the above embodiment, and is specifically as follows:

[0066] When starting the main engine 1, the integrated energy management system 3 drives the starter generator 4 to drive the high-pressure shaft 17 to rotate until the combustion chamber 13 is successfully injected and ignited, so that the main engine 1 is started. After the main engine 1 is successfully started, the starter generator 4 is converted to the engine mode to supply power to the main engine 1 and the aircraft;

[0067] When the aircraft takes off, the integrated energy management system 3 controls the generator 6 to output a small amount of power to the ducted fan 2, driving the ducted fan 2 to operate at a low power;

[0068] When the aircraft is cruising, the integrated energy management system 3 controls the generator 6 to increase the power output to the ducted fan 2, driving the ducted fan 2 to operate at high power;

[0069] When the aircraft needs greater thrust, the hydrogen combustion chamber of the ducted fan 2 is controlled to operate.

[0070] The aircraft hybrid power system control method disclosed in the above embodiment is used to realize the control of the aircraft hybrid power system disclosed in the above embodiment. The description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft hybrid power system part. Its technical effect can also refer to the technical effect of the relevant part of the aircraft hybrid power system, which will not be repeated here.

[0071] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft hybrid power system, characterized in that: It includes a main engine (1), a ducted fan (2), a generator (4), a cooling fan (5), a generator (6), and a lubricating oil pipeline (7); The main engine (1) is arranged at the tail of the aircraft and is a high bypass ratio turbofan engine, comprising a fan (11), a compressor (12), a combustion chamber (13), a high pressure turbine (14), a low pressure turbine (15), and a nozzle (16) which are arranged in sequence; A generator (4) and a cooling fan (5) are arranged in the front cavity of the main engine (1); the generator (4) is connected to the high-pressure shaft (17) of the main engine (1); the cooling fan (5) is connected to the low-pressure shaft (18) of the main engine (1); the cooling fan (5) is located in front of the generator (4); and the generator (4) is connected to the main engine (1) and the power system of the aircraft; A generator (6) is arranged in the rear cavity of the main engine (1) and a lubricating oil pipeline (7) is inserted therein, and the generator (6) is connected to a low-pressure shaft (18); There are two ducted fans (2), which are arranged under the two wings, connected to the generator (6), and are provided with a hydrogen combustion chamber; The ducted fan (2) comprises an outer casing (21), a guide cone (22), an electric fan (23), a rectifying support plate (24), a hydrogen injection rod (25), an ignition nozzle (29), and an electric motor (210); The guide cone (22) is arranged in the outer casing (21) and has an annular gap at the front end; The electric fan (23) is arranged in the outer casing (21) and is located in the annular gap; There are a plurality of rectifying support plates (24), which are supported between the outer casing (21) and the guide cone (22) along the circumferential direction, are located behind the electric fan (23), and form a hydrogen combustion chamber between the outer casing (21) and the guide cone (22); There are a plurality of hydrogen injection rods (25), which are arranged through the outer casing (21) and extend into each rectifying support plate (24), and the injection nozzles extend from the two side walls of the rectifying support plate (24); The ignition nozzle (29) is arranged through the outer casing (21) and extends into the hydrogen combustion chamber; The electric motor (210) is arranged in the guide cone (22), connected to the generator (6) via a line, and its rotating shaft is connected to the electric fan (23).

2. The aircraft hybrid power system according to claim 1, characterized in that: It also includes an integrated energy management system (3); The integrated energy management system (3) is arranged outside the main engine (1); The generator (4) is connected to the integrated energy management system (3); The generator (6) is connected to the integrated energy management system (3).

3. The aircraft hybrid power system according to claim 2, characterized in that: The ducted fan (2) further comprises an annular pipe (26), a high-pressure hydrogen storage tank (27), and a one-way opening and closing valve (28); The annular tube (26) is sleeved on the outer periphery of the outer casing (21), connected to each hydrogen injection rod (25), and connected to the high-pressure hydrogen storage tank (27) through a pipeline, and a one-way opening and closing valve (28) is provided on the pipeline connected to the high-pressure hydrogen storage tank (27).

4. A method for controlling an aircraft hybrid power system, for controlling the aircraft hybrid power system according to claim 3, characterized in that: include: When starting the main engine (1), the integrated energy management system (3) drives the starter generator (4) to drive the high-pressure shaft (17) to rotate until the combustion chamber (13) is successfully injected with fuel and ignited, so that the main engine (1) is started. After the main engine (1) is successfully started, the starter generator (4) is converted into a power generation mode to supply power to the main engine (1) and the aircraft; When the aircraft takes off, the integrated energy management system (3) controls the generator (6) to output power to the ducted fan (2), thereby driving the ducted fan (2) to operate at low power; When the aircraft is cruising, the integrated energy management system (3) controls the generator (6) to increase the power output to the ducted fan (2), thereby driving the ducted fan (2) to operate at high power; When the aircraft requires greater thrust, the hydrogen combustion chamber of the ducted fan (2) is controlled to operate.

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