An aeroengine with an integrated motor

Abstract

The application belongs to the technical field of aero-engine design, and particularly relates to an aero-engine with a built-in motor. The aero-engine is designed to set a start generator in the main engine, extract power from a high-pressure shaft and a low-pressure shaft of the generator, convert the power into electric energy, supply the electric energy to a lubricating oil pump, an electric supercharging pump, an electric fuel pump, a nozzle supercharging pump, a nozzle oil source pump and an aircraft power supply system as needed, and store the excess electric energy to a storage battery as a supplement when power supply is insufficient, so that the power supply to the aircraft can be ensured, the situation of insufficient power supply to the aircraft can be avoided, and the loss of useless power can be avoided.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine design, and particularly relates to an aero-engine with an embedded motor. BACKGROUND

[0002] A traditional turbine engine provides secondary energy for an airplane through bleed air and mechanical transmission. The bleed air from the engine to the airplane causes waste of high-pressure air of the engine and has a great influence on the performance of the engine. The mechanical transmission extracts power from the engine to the airplane through an engine accessory case, an airplane accessory case, a transmission flexible shaft and the like, and the system is complex, heavy and prone to failure. Moreover, the power extracted from the engine is related to the state of the engine and cannot be adjusted, and there is a situation of insufficient power supply to the airplane. Therefore, a secondary power system needs to be provided on the airplane.

[0003] The multi-electric airplane technology is a new technology in the development of aviation, and electric energy will become the only secondary energy on the airplane. Therefore, an engine needs to be designed to provide sufficient electric energy for the airplane. In view of this, the application is proposed. SUMMARY

[0004] The purpose of the application is to provide an aero-engine with an embedded motor to overcome or alleviate at least one aspect of the known technical defects.

[0005] The technical solution of the application is as follows:

[0006] An aero-engine with an embedded motor comprises an engine main machine, a start generator, a generator, an electric control system and a storage battery.

[0007] The electric control system and the storage battery are arranged outside the engine main machine. The electric control system is connected to the storage battery through a line, and is connected to a lubricating oil pump, an electric supercharging pump, an electric fuel pump, a nozzle supercharging pump and a nozzle oil source pump of the engine main machine through lines, and is connected to an airplane power supply system through a line.

[0008] The start generator is arranged in a front cavity of the engine main machine, is sleeved on a front end of a high-pressure shaft of the engine main machine, and is connected to the electric control system through a line.

[0009] The generator is arranged in a rear cavity of the engine main machine, and is sleeved on a rear end of a low-pressure shaft of the engine main machine.

[0010] When starting the engine main machine, the electric control system sets the start generator to an electric mode, controls the storage battery to supply power to the start generator, drives the high-pressure shaft to rotate, and ignites the engine main machine when the rotation speed of the high-pressure shaft reaches a required rotation speed, so as to start the engine main machine.

[0011] After the engine main machine starts, the electric control system sets the starter generator to the power generation mode, so that the starter generator works in the power generation mode and generates power under the drive of the high-pressure shaft, and the generator generates power under the drive of the low-pressure shaft, and the power generated by the starter generator and the generator is supplied to the oil pump, the electric supercharger pump, the electric fuel pump, the nozzle supercharger pump, the nozzle oil source pump and the aircraft power supply system according to the demand, and the excess power is stored in the storage battery.

[0012] Optionally, in the aviation engine with the built-in motor, when the power generated by the starter generator and the generator is insufficient to meet the power demand of the oil pump, the electric supercharger pump, the electric fuel pump, the nozzle supercharger pump, the nozzle oil source pump and the aircraft power supply system, the electric control system controls the storage battery to supply power to the oil pump, the electric supercharger pump, the electric fuel pump, the nozzle supercharger pump, the nozzle oil source pump and the aircraft power supply system.

[0013] Optionally, in the aviation engine with the built-in motor, the electric control system can collect the rotation speed signals of the starter generator and the generator, and then obtain the working state of the engine main machine and the power demand of the oil pump, the electric supercharger pump, the electric fuel pump, the nozzle supercharger pump and the nozzle oil source pump, so as to realize the on-demand power supply of the oil pump, the electric supercharger pump, the electric fuel pump, the nozzle supercharger pump and the nozzle oil source pump.

[0014] Optionally, in the aviation engine with the built-in motor, the line connected with the electric control system of the starter generator is routed from the front support plate of the engine main machine.

[0015] Optionally, in the aviation engine with the built-in motor, the line connected with the electric control system of the generator is routed from the rear support plate of the engine main machine.

[0016] Optionally, in the aviation engine with the built-in motor, the aviation engine further comprises an air bleed pipe and an exhaust pipe.

[0017] The air bleed pipe is connected with the front cavity of the engine main machine and the flow channel of the compressor.

[0018] The exhaust pipe is connected with the front cavity of the engine main machine and the outer duct.

[0019] Optionally, in the aviation engine with the built-in motor, the aviation engine further comprises an oil inlet pipe and an oil return pipe.

[0020] The oil inlet pipe is connected with the rear cavity of the engine main machine and the external oil tank.

[0021] The oil return pipe is connected with the rear cavity of the engine main machine and the external oil tank.

[0022] The present application has at least the following beneficial technical effects:

[0023] The application provides an aero-engine with an embedded motor, which is designed to extract power from a starter generator arranged in an engine main machine, convert the power into electric energy, supply the electric energy to a lubricating oil pump, an electric supercharging pump, an electric fuel pump, a nozzle supercharging pump, a nozzle oil source pump and an aircraft power supply system, and store the excess electric energy in a storage battery as a supplement when power supply is insufficient, so as to ensure the power supply to the aircraft and avoid the situation of insufficient power supply to the aircraft and the loss of useless power. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 FIG. 1 is a schematic diagram of an aero-engine with an embedded motor provided by the application;

[0025] Figure 2 FIG. 2 is a schematic diagram of the aero-engine with an embedded motor provided by the application and the appearance of an existing engine;

[0026] Figure 3 FIG. 3 is a schematic diagram of the aero-engine with an embedded motor provided by the application and the cooling of a starter generator and a generator thereof;

[0027] Wherein:

[0028] 1-engine main machine; 2-starter generator; 3-generator; 4-electric control system; 5-storage battery; 6-lubricating oil pump; 7-electric supercharging pump; 8-electric fuel pump; 9-nozzle supercharging pump; 10-nozzle oil source pump; 11-high pressure shaft; 12-low pressure shaft; 13-compressor; 14-blow-off pipe; 15-exhaust pipe; 16-low pressure turbine; 17-lubricating oil inlet pipe; 18-lubricating oil return pipe; 19-fan.

[0029] In order to better illustrate the embodiments, some contents in the drawings are omitted, enlarged or reduced, which are only used for exemplary illustration and cannot be understood as a limitation to the application. DETAILED DESCRIPTION

[0030] In order to make the technical solutions of the application and the advantages thereof clearer, the technical solutions of the application will be further clearly and completely described below with reference to the drawings, and it should be understood that the specific embodiments described herein are only some embodiments of the application, which are used to explain the application, but not to limit the application. It should be noted that, in order to facilitate the description, only parts related to the application are shown in the drawings, and other related parts can be referred to the general design.

[0031] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of the application should be the general meanings understood by the general technical personnel in the field of the application. In the description of the application, "including" indicates that the concept appearing before the word covers the concepts listed after the word and its equivalents, and does not exclude other associated concepts.

[0032] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a 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. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0033] 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 storage battery 5.

[0034] The electronic control system 4 and the battery 5 are installed outside the engine main unit 1. The electronic control system 4 is connected to the battery 5 via wiring, and also to the oil pump 6, electric booster pump 7, electric fuel pump 8, nozzle booster pump 9, and nozzle fuel source pump 10 of the engine main unit 1 via wiring, and is connected to the aircraft power supply system via wiring. The oil pump 6 is used to draw oil from the oil tank to supply lubricating and cooling components such as bearings in the engine main unit 1; the electric booster pump 7 is used to draw fuel from the aircraft fuel tank; the electric fuel pump 8 is used to boost the fuel drawn by the electric booster pump 7 to supply combustion chamber of the engine main unit 1; the nozzle booster pump 9 is used to draw fuel from the aircraft fuel tank; and the nozzle fuel source pump 10 is used to boost the fuel drawn by the nozzle booster pump 9, thereby providing hydraulic pressure to the nozzle actuation system of the engine main unit 1 to drive the nozzle to contract and expand.

[0035] The generator 2 is installed in the front cavity of the engine host 1 and is sleeved on the front end of the high-voltage shaft 11 of the engine host 1. It is connected to the electronic control system 4 through a line, which can be routed from the front support plate of the engine host 1.

[0036] The generator 3 is installed in the rear cavity of the engine host 1 and is sleeved on the rear end of the low-pressure shaft 12 of the engine host 1. It is connected to the electronic control system 4 through a line, which can be routed from the rear support plate of the engine host 1.

[0037] The aircraft engine with a built-in motor disclosed in the above embodiments can start the engine main unit 1 by setting the generator 2 to electric mode through the electronic control system 4 and controlling the battery 5 to supply power to the generator 2, so that the 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 high-voltage shaft 11 reaches the speed required for engine ignition, the engine main unit 1 is ignited, and the engine main unit 1 is started.

[0038] After the engine main machine 1 starts, the electric 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 power under the drive of the high-pressure shaft 11. At the same time, the generator 3 generates power under the drive of the low-pressure shaft 12. The power generated by the starter-generator 2 and the generator 3 is supplied to the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, the nozzle oil source pump 10, and the aircraft power supply system as needed, and the excess power is stored in the storage battery 5.

[0039] When the power generated by the starter-generator 2 and the generator 3 is insufficient to meet the power demand of the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, the nozzle oil source pump 10, and the aircraft power supply system, the electric control system 4 controls the storage battery 5 to supply power to the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, the nozzle oil source pump 10, and the aircraft power supply system.

[0040] The electric control system 4 can collect the rotation speed signals of the starter-generator 2 and the generator 3, that is, the rotation speed signals of the high-pressure shaft 11 and the low-pressure shaft 12, so as to obtain the working state of the engine main machine 1 and the power demand of the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, and the nozzle oil source pump 10, and supply power to the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, and the nozzle oil source pump 10 as needed, so as to reduce power loss.

[0041] The aircraft engine with the 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 starter-generator 2 and the generator 3 arranged in the engine main machine 1, convert the power into electric energy, supply the electric energy to the oil pump 6, the electric supercharging pump 7, the electric fuel pump 8, the nozzle supercharging pump 9, the nozzle oil source pump 10, and the aircraft power supply system as needed, and store the excess electric energy in the storage battery 5 as a supplement when the power supply is insufficient, so as to ensure the power supply to the aircraft and avoid the situation that the power supply to the aircraft is insufficient, and avoid the loss of useless power.

[0042] The aircraft engine with the built-in motor disclosed in the above embodiment no longer provides secondary energy to the aircraft through bleed air and mechanical transmission, which can reduce the influence on the performance of the engine main machine 1, and cancel the engine accessory case, the aircraft accessory case, the transmission flexible shaft, and other structures outside the engine main machine 1, which can reduce the complexity, weight, and mechanical failure of the engine system. In addition, the shape of the engine main machine 1 can be designed as a regular circle, which can effectively reduce the wind area compared with the existing drum-shaped engine, as shown in FIG. 1. Figure 2

[0043] ​The starter generator 2 is arranged in the front cavity of the engine main machine 1, behind the fan 19 of the engine main machine 1, in a lower temperature environment, and can be directly cooled by the bleed air of the compressor 13 of the engine main machine 1. The specific design can refer to Figure 3 The bleed air pipe 14 is connected to the front cavity of the engine main machine 1 and the flow channel of the compressor 13, and the bleed air is introduced from the second stage of the compressor 13 to the front cavity to cool the starter generator 2. The exhaust pipe 15 is connected to the front cavity of the engine main machine 1 and the outer channel, and the bleed air entering the front cavity is discharged to the outer channel.

[0044] The generator 3 is arranged in the rear cavity of the engine main machine 1, behind the low-pressure turbine 16 of the engine main machine 1, in a higher temperature environment, and can be cooled by the lubricating oil. The specific design can refer to Figure 3 The lubricating oil inlet pipe 17 is connected to the rear cavity of the engine main machine 1 and the external lubricating oil tank, and the lubricating oil is introduced into the rear cavity to cool the generator 3. The lubricating oil return pipe 18 is connected to the rear cavity of the engine main machine 1 and the external lubricating oil tank, and the lubricating oil entering the rear cavity is returned to the external lubricating oil tank.

[0045] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings. It should be understood by those skilled in the art that the protection scope of the present application is obviously not limited to these specific embodiments. Those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

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

2. The aircraft engine with a built-in motor according to claim 1, characterized in that, When the electrical energy generated by the generator (2) and generator (3) is insufficient to meet the power requirements of the lubricating oil pump (6), electric booster pump (7), electric fuel pump (8), nozzle booster pump (9), nozzle oil source pump (10) and aircraft power supply system, the electronic control system (4) controls the storage battery (5) to supply power to the lubricating oil pump (6), electric booster pump (7), electric fuel pump (8), nozzle booster pump (9), nozzle oil source pump (10) and 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 speed signals of the generator (2) and generator (3), thereby obtaining the working status of the engine host (1) and the power demand of the lubricating oil pump (6), electric booster pump (7), electric fuel pump (8), nozzle booster pump (9), and nozzle oil source pump (10), so as to realize the on-demand supply of electrical energy to the lubricating oil pump (6), electric booster pump (7), electric fuel pump (8), nozzle booster pump (9), and nozzle oil source pump (10).

4. The aircraft engine with a built-in electric motor according to claim 3, characterized in that, The wiring connecting the generator (2) to the electronic control system (4) is routed from the front support plate of the engine host (1).

5. The aircraft engine with a built-in electric motor according to claim 4, characterized in that, The wiring connecting the generator (3) to the electronic control system (4) is routed from the rear support plate of the engine host (1).

6. The aircraft engine with a built-in electric motor according to claim 5, characterized in that, It also includes an air intake pipe (14) and an exhaust pipe (15); The air intake pipe (14) connects the front chamber of the engine main unit (1) and the flow passage of the compressor (13); The exhaust pipe (15) connects to the front cavity and the outer bypass of the engine host (1).

7. The aircraft engine with a built-in electric 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) connects to the rear cavity of the engine main unit (1) and the external lubricating oil tank; The lubricating oil return pipe (18) connects to the rear cavity of the engine host (1) and the external lubricating oil tank.

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