Aero-engine with built-in motor

Abstract

The invention belongs to the technical field of aero-engine design, and particularly relates to an aero-engine with a built-in motor, which is designed to be characterized in that a generator is arranged in an engine main engine, and the generator extracts power from a high-pressure shaft and a low-pressure shaft and converts the power into electric energy; the electric energy is supplied to a lubricating oil pump, an electric booster pump, an electric fuel pump, a nozzle booster pump, a nozzle oil source pump and an aircraft power supply system according to needs, redundant electric energy is stored in a storage battery to serve as supplement when power supply is insufficient, power supply to an aircraft can be guaranteed, the situation that power supply to the aircraft is insufficient is avoided, and loss of useless power can be avoided.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine design, and specifically relates to an aircraft engine with a built-in motor. Background Art

[0002] Traditional turbine engines provide secondary energy for aircraft through bleed air and mechanical transmission. Bleed air from the engine to the aircraft will cause waste of engine high-pressure air and have a significant impact on engine performance. Mechanical transmission extracts power from the engine to the aircraft through the engine accessory casing, aircraft accessory casing, transmission flexible shaft, etc. The system is complex, heavy, and prone to failure. In addition, the power extracted from the engine is related to the engine status and cannot be adjusted, resulting in insufficient power supply to the aircraft. For this reason, a second power system needs to be installed on the aircraft.

[0003] More-electric aircraft technology is an emerging technology in the development of aviation. Electricity will become the only secondary energy source on aircraft, and electrical systems will replace hydraulic, pneumatic, mechanical and other power systems. To this end, it is necessary to design engines that can provide sufficient electrical energy for the aircraft. In view of this, this application is filed. Summary of the invention

[0004] The purpose of the present application is to provide an aircraft engine with a built-in electric motor to overcome or alleviate at least one of the known technical deficiencies.

[0005] The technical solution of this application is: An aircraft engine with a built-in motor, comprising: an engine main engine, a starter generator, a generator, an electronic control system, and a battery; The electronic control system and the battery are arranged outside the main engine. The electronic control system is connected to the battery through lines, and is also connected to the lubricating oil pump, electric boost pump, electric fuel pump, nozzle boost pump, and nozzle oil source pump of the main engine through lines, and is also connected to the aircraft power supply system through lines; The generator is arranged in the front cavity of the engine main engine, sleeved on the front end of the high-voltage shaft of the engine main engine, and connected to the electronic control system through lines.

[0006] The generator is arranged in the rear cavity of the engine main engine and is sleeved on the rear end of the low-pressure shaft of the engine main engine; When starting the main engine, the electronic control system sets the starter generator to the electric mode and controls the battery to supply power to the starter generator, so that the starter generator drives the high-voltage shaft to rotate. After the high-voltage shaft speed reaches the speed required for engine ignition, the main engine is ignited to start the main engine; After the engine main engine is started, the electronic control system sets the starter generator to the power generation mode, so that the starter generator works in the power generation mode and generates electricity driven by the high-pressure shaft. At the same time, the generator generates electricity driven by the low-pressure shaft. The electric energy generated by the starter generator and the generator is supplied to the lubricating oil pump, electric boost pump, electric fuel pump, nozzle boost pump, nozzle oil source pump and the aircraft power supply system as needed, and the excess electric energy is stored in the battery.

[0007] Optionally, in the above-mentioned aircraft engine with a built-in motor, when the electric energy generated by the starter and the generator is not sufficient to meet the power demand of the lubricating oil pump, the electric boost pump, the electric fuel pump, the nozzle boost pump, the nozzle oil source pump and the aircraft power supply system, the electronic control system controls the battery to supply power to the lubricating oil pump, the electric boost pump, the electric fuel pump, the nozzle boost pump, the nozzle oil source pump and the aircraft power supply system.

[0008] Optionally, in the above-mentioned aircraft engine with a built-in motor, the electronic control system can collect the speed signals of the generator and the generator, and then derive the working status of the engine main engine, and obtain the power demand of the lubricating oil pump, electric boost pump, electric fuel pump, nozzle boost pump, and nozzle oil source pump, so as to supply electric energy to the lubricating oil pump, electric boost pump, electric fuel pump, nozzle boost pump, and nozzle oil source pump on demand.

[0009] Optionally, in the above-mentioned aircraft engine with a built-in motor, the line connecting the generator to the electronic control system is routed through the front support plate of the engine main body.

[0010] Optionally, in the above-mentioned aircraft engine with a built-in motor, the line connecting the generator to the electronic control system is routed through the rear support plate of the engine main body.

[0011] Optionally, the above-mentioned aircraft engine with a built-in motor further includes an air duct and an exhaust pipe; The air bleed pipe connects the front chamber of the engine main engine and the flow passage of the compressor; The exhaust pipe is connected to the front cavity and the outer duct of the engine main engine.

[0012] Optionally, the above-mentioned aircraft engine with a built-in motor further includes a lubricating oil inlet pipe and a lubricating oil return pipe; The lubricating oil inlet pipe is connected to the rear cavity of the engine main engine and the external lubricating oil tank; The lubricating oil return pipe is connected to the rear cavity of the engine main engine and the external lubricating oil tank.

[0013] This application has at least the following beneficial technical effects: Provided is an aircraft engine with a built-in motor, which is designed so that a starter and a generator arranged in the main engine can extract power from a high-pressure shaft and a low-pressure shaft, convert the power into electrical energy, and supply the power to a lubricating oil pump, an electric boost pump, an electric fuel pump, a nozzle boost pump, a nozzle oil source pump and an aircraft power supply system as needed, and store the excess electrical energy in a battery as a supplement when the power supply is insufficient, thereby ensuring the power supply to the aircraft, avoiding the situation of insufficient power supply to the aircraft, and avoiding the loss of useless power. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a schematic diagram of an aircraft engine with a built-in motor provided in an embodiment of the present application; Figure 2 It is a schematic diagram comparing the appearance of an aircraft engine with a built-in motor provided in an embodiment of the present application with that of an existing engine; Figure 3 It is a schematic diagram of a generator and its cooling for an aircraft engine with a built-in motor provided in an embodiment of the present application; in: 1-Engine main engine; 2-Starter generator; 3-Generator; 4-Electronic control system; 5-Battery; 6-Lubricating oil pump; 7-Electric boost pump; 8-Electric fuel pump; 9-Nozzle boost pump; 10-Nozzle oil source pump; 11-High pressure shaft; 12-Low pressure shaft; 13-Compressor; 14-Bleed pipe; 15-Exhaust pipe; 16-Low pressure turbine; 17-Lubricating oil inlet pipe; 18-Lubricating oil return pipe; 19-Fan.

[0015] 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

[0016] 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.

[0017] 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.

[0018] 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.

[0019] An aircraft engine with a built-in electric motor, such as Figure 1 As shown, it includes an engine main unit 1, a starter generator 2, a generator 3, an electronic control system 4, and a battery 5.

[0020] The electronic control system 4 and the battery 5 are arranged outside the engine main body 1. The electronic control system 4 is connected to the battery 5 through lines, and is also connected to the lubricating oil pump 6, the electric boosting pump 7, the electric fuel pump 8, the nozzle boosting pump 9, and the nozzle oil source pump 10 of the engine main body 1 through lines, and is connected to the aircraft power supply system through lines, wherein the lubricating oil pump 6 is used to extract lubricating oil from the lubricating oil tank and supply it to bearings and other components in the engine main body 1 for lubrication and cooling; the electric boosting pump 7 is used to extract fuel from the aircraft fuel tank; the electric fuel pump 8 is used to pressurize the fuel extracted by the electric boosting pump 7 and supply it to the combustion chamber of the engine main body 1 for combustion; the nozzle boosting pump 9 is used to extract fuel from the aircraft fuel tank; the nozzle oil source pump 10 is used to pressurize the fuel extracted by the nozzle boosting pump 9, and then provide hydraulic pressure for the nozzle actuation system of the engine main body 1 to drive the nozzle mouth to contract and expand.

[0021] The generator 2 is arranged in the front cavity of the engine main body 1, sleeved on the front end of the high-pressure shaft 11 of the engine main body 1, and connected to the electronic control system 4 through a line, and the line can be routed from the front support plate of the engine main body 1.

[0022] The generator 3 is arranged in the rear cavity of the engine main body 1, sleeved on the rear end of the low-pressure shaft 12 of the engine main body 1, and connected to the electronic control system 4 through a line, and the line can be routed from the rear support plate of the engine main body 1.

[0023] The aircraft engine with a built-in motor disclosed in the above embodiment can start the engine main unit 1 by setting the starter generator 2 to the electric mode through the electronic control system 4, and control the battery 5 to supply power to the starter generator 2, so that the starter generator 2 drives the high-voltage shaft 11 to rotate, that is, drives the high-voltage rotor of the engine main unit 1 to rotate. After the speed of the high-voltage shaft 11 reaches the speed required for engine ignition, the engine main unit 1 is ignited to start the engine main unit 1.

[0024] After the engine main unit 1 is started, the electronic control system 4 can set the starter generator 2 to the power generation mode, so that the starter generator 2 works in the power generation mode and generates electricity under the drive of the high-pressure shaft 11. At the same time, the generator 3 will generate electricity under the drive of the low-pressure shaft 12. The electric energy generated by the starter generator 2 and the generator 3 is supplied to the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, the nozzle oil source pump 10 and the aircraft power supply system as needed, and the excess electric energy is stored in the battery 5.

[0025] When the electric energy generated by the generator 2 and the generator 3 is not sufficient to meet the power demand of the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, the nozzle oil source pump 10 and the aircraft power supply system, the electronic control system 4 can control the battery 5 to supply power to the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, the nozzle oil source pump 10 and the aircraft power supply system.

[0026] The electronic control system 4 can collect the speed signals of the generator 2 and the generator 3, that is, collect the speed signals of the high-pressure shaft 11 and the low-pressure shaft 12, and then can obtain the working state of the engine main unit 1, and obtain the power demand of the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, and the nozzle oil source pump 10, thereby realizing the on-demand supply of electric energy to the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, and the nozzle oil source pump 10 to reduce power loss.

[0027] The aircraft engine with built-in motor disclosed in the above embodiment is designed to extract power from the high-pressure shaft 11 and the low-pressure shaft 12 by the generator 2 and the generator 3 arranged in the engine main body 1, and convert it into electrical energy, and supply the lubricating oil pump 6, the electric boost pump 7, the electric fuel pump 8, the nozzle boost pump 9, the nozzle oil source pump 10 and the aircraft power supply system as needed, and store the excess electrical energy in the battery 5 as a supplement when the power supply is insufficient, so as to ensure the power supply to the aircraft, avoid the situation of insufficient power supply to the aircraft, and avoid the loss of useless power.

[0028] The aircraft engine with built-in motor disclosed in the above embodiment no longer provides secondary energy to the aircraft by means of air bleed and mechanical transmission, which can reduce the impact on the performance of the engine main engine 1, and eliminate the engine accessory casing, aircraft accessory casing, transmission flexible shaft and other structures outside the engine main engine 1, which can reduce the complexity of the engine system and its weight, and mechanical failures. In addition, the shape of the engine main engine 1 can be designed to be a regular circle, which can effectively reduce the frontal area compared to the existing bulge-type engine, such as Figure 2 shown.

[0029] The generator 2 is arranged in the front cavity of the engine main body 1, behind the fan 19 of the engine main body 1, and the ambient temperature is relatively low. It can be designed to be directly cooled by the bleed air of the compressor 13 of the engine main body 1. For specific design, please refer to Figure 3 An air bleed pipe 14 is used to connect the front cavity of the engine main body 1 and the flow path of the compressor 13, and air is bleed into the front cavity from the second stage of the compressor 13 to cool the generator 2. An exhaust pipe 15 is provided to connect the front cavity and the outer duct of the engine main body 1, and the bleed air entering the front cavity is discharged into the outer duct.

[0030] The generator 3 is arranged in the rear cavity of the engine main body 1, behind the low-pressure turbine 16 of the engine main body 1. The ambient temperature is relatively high, and it can be designed to be cooled by lubricating oil. For specific design, please refer to Figure 3 The lubricating oil inlet pipe 17 is connected to the rear cavity of the engine main unit 1 and the external lubricating oil tank, and the lubricating oil is introduced into the rear cavity to cool the generator 3. A lubricating oil return pipe 18 is provided to connect the rear cavity of the engine main unit 1 and the external lubricating oil tank, so that the lubricating oil entering the rear cavity flows back to the external lubricating oil tank.

[0031] 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 engine with a built-in motor, characterized in that: include: Engine main unit (1), generator (2), generator (3), electronic control system (4), battery (5); The electronic control system (4) and the storage battery (5) are arranged outside the main engine (1). The electronic control system (4) is connected to the storage battery (5) through a line, and is also connected to the lubricating oil pump (6), the electric boost pump (7), the electric fuel pump (8), the nozzle boost pump (9), and the nozzle oil source pump (10) of the main engine (1) through a line, and is also connected to the aircraft power supply system through the line. The generator (2) is arranged in the front cavity of the engine main unit (1), is sleeved on the front end of the high-pressure shaft (11) of the engine main unit (1), and is connected to the electronic control system (4) via a line. The generator (3) is arranged in the rear cavity of the main engine (1) and is sleeved on the rear end of the low-pressure shaft (12) of the main engine (1); When the engine main unit (1) is started, the electronic control system (4) sets the starter generator (2) to an electric mode and controls the storage battery (5) to supply power to the starter generator (2), so that the starter generator (2) drives the high-voltage shaft (11) to rotate, and after the rotation speed of the high-voltage shaft (11) reaches the rotation speed required for engine ignition, the engine main unit (1) is ignited, so that the engine main unit (1) is started; After the engine main engine (1) is started, the electronic control system (4) sets the starter generator (2) to a power generation mode, so that the starter generator (2) operates in the power generation mode and generates electricity under the drive of the high-pressure shaft (11). At the same time, the generator (3) generates electricity under the drive of the low-pressure shaft (12). The electric energy generated by the starter generator (2) and the generator (3) is supplied to the lubricating oil pump (6), the electric boost pump (7), the electric fuel pump (8), the nozzle boost pump (9), the nozzle oil source pump (10) and the aircraft power supply system as required, and the excess electric energy is stored in the storage battery (5).

2. The aircraft engine with a built-in motor according to claim 1, characterized in that: When the electric energy generated by the generator (2) and the generator (3) is insufficient to meet the power demand of the lubricating oil pump (6), the electric boost pump (7), the electric fuel pump (8), the nozzle boost pump (9), the nozzle oil source pump (10) and the aircraft power supply system, the electronic control system (4) controls the storage battery (5) to supply power to the lubricating oil pump (6), the electric boost pump (7), the electric fuel pump (8), the nozzle boost pump (9), the nozzle oil source pump (10) and the aircraft power supply system.

3. The aircraft engine with a built-in motor according to claim 2, characterized in that: The electronic control system (4) can collect the rotation speed signals of the generator (2) and the generator (3), thereby obtaining the working state of the engine main unit (1), and obtaining the power demand of the lubricating oil pump (6), the electric boosting pump (7), the electric fuel pump (8), the nozzle boosting pump (9), and the nozzle oil source pump (10), thereby supplying electric energy to the lubricating oil pump (6), the electric boosting pump (7), the electric fuel pump (8), the nozzle boosting pump (9), and the nozzle oil source pump (10) on demand.

4. The aircraft engine with a built-in motor according to claim 3, characterized in that: The line connecting the generator (2) to the electronic control system (4) is routed through the front support plate of the engine main unit (1).

5. The aircraft engine with a built-in motor according to claim 4, characterized in that: The line connecting the generator (3) to the electronic control system (4) is routed through the rear support plate of the engine main unit (1).

6. The aircraft engine with a built-in motor according to claim 5, characterized in that: It also includes an air duct (14) and an exhaust duct (15); An air bleed pipe (14) connected to the front chamber of the engine main unit (1) and the flow passage of the compressor (13); The exhaust pipe (15) is connected to the front chamber and the outer duct of the engine main unit (1).

7. The aircraft engine with a built-in motor according to claim 6, characterized in that: It also includes a lubricating oil inlet pipe (17) and a lubricating oil return pipe (18); The lubricating oil inlet pipe (17) is connected to the rear chamber of the engine main unit (1) and the external lubricating oil tank; The lubricating oil return pipe (18) is connected to the rear chamber of the engine main unit (1) and the external lubricating oil tank.

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