CN117644979A - Double-motor hybrid aeroengine - Google Patents
Double-motor hybrid aeroengine Download PDFInfo
- Publication number
- CN117644979A CN117644979A CN202410123019.9A CN202410123019A CN117644979A CN 117644979 A CN117644979 A CN 117644979A CN 202410123019 A CN202410123019 A CN 202410123019A CN 117644979 A CN117644979 A CN 117644979A
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- China
- Prior art keywords
- motor
- shaft
- working mode
- transmission gear
- dual
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 230000005611 electricity Effects 0.000 claims abstract description 8
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 claims description 44
- 238000004146 energy storage Methods 0.000 claims description 26
- 239000000446 fuel Substances 0.000 claims description 9
- 239000010687 lubricating oil Substances 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 6
- 239000000314 lubricant Substances 0.000 description 3
- 230000009977 dual effect Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000284 extract Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000007537 lampworking Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Hybrid Electric Vehicles (AREA)
Abstract
The invention provides a hybrid aeroengine with double motors, comprising: a core machine having a high pressure shaft; the first motor is connected with the high-voltage shaft and is provided with a first working mode and a second working mode, the first motor can drive the high-voltage shaft to rotate in the first working mode, and the high-voltage shaft can drive the first motor to rotate to generate electricity in the second working mode; the fan shaft is arranged at a distance from the high-pressure shaft and is positioned at the upstream position of the high-pressure shaft; the second motor is connected with the fan shaft and is provided with a third working mode and a fourth working mode, the second motor can drive the fan shaft to rotate in the third working mode, and the fan shaft can drive the second motor to rotate to generate electricity in the fourth working mode. According to the invention, four working modes can be switched by additionally arranging the first motor and the second motor, so that the core machine works in a high-efficiency state for a long time, and the working efficiency of the engine is improved.
Description
Technical Field
The specification relates to the technical field of aeroengines, in particular to a hybrid aeroengine with double motors.
Background
In recent years, with the development of energy storage battery technology and high-speed motor technology, a new revolution of electrified energy system technology represented by electric propulsion technology is reconstructing the global aviation and ground transportation industry pattern, and is regarded as an important mark for the aviation industry to enter the third era, and high attention is paid to the main aviation state in the world. Electrification of aviation propulsion systems has a variety of implementation paths, limited by current battery energy density levels, hybrid electric propulsion systems are a near-medium-term focus research direction. Hybrid electric propulsion technology has been widely adopted in the automotive industry and has proven to be an effective technology. At present, the aviation industry in various countries regards a hybrid electric propulsion system as a promising civil and military aviation power solution which has potential to be put into use after 2030 and is accelerating.
Hybrid electric propulsion systems are propulsion systems that are powered by both an aircraft gas turbine engine and an energy storage battery. The high-voltage rotor and the low-voltage rotor of the conventional aero-engine have a coupling relation, and the core engine is difficult to be in a high-efficiency working state for a long time, so that an innovative hybrid aero-engine is required to be provided for realizing the optimal performance of the hybrid electric propulsion system under different use conditions, and the high-efficiency working state of the core engine is realized for a long time when the core engine works. Meanwhile, more hybrid electric propulsion systems currently adopt a distributed configuration, which increases the complexity of the overall system and requires a more centralized configuration scheme.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide a hybrid aeroengine with dual motors to achieve the purpose of high-efficiency operation of the engine under different working conditions.
The technical scheme of the invention is as follows: a dual-motor hybrid aircraft engine comprising: a core machine having a high pressure shaft; the first motor is connected with the high-voltage shaft and is provided with a first working mode and a second working mode, the first motor can drive the high-voltage shaft to rotate in the first working mode, and the high-voltage shaft can drive the first motor to rotate to generate electricity in the second working mode; the fan shaft is arranged at a distance from the high-pressure shaft and is positioned at the upstream position of the high-pressure shaft; the second motor is connected with the fan shaft and is provided with a third working mode and a fourth working mode, the second motor can drive the fan shaft to rotate in the third working mode, and the fan shaft can drive the second motor to rotate to generate electricity in the fourth working mode.
Further, the hybrid aeroengine with the double motors further comprises an energy storage battery pack, and the first motor and the second motor are connected with the energy storage battery pack.
Further, a first transmission gear is arranged on the high-voltage shaft, a second transmission gear is arranged on the first motor, and the first transmission gear and the second transmission gear are meshed for transmission.
Further, a third transmission gear is arranged on the fan shaft, a fourth transmission gear is arranged on the second motor, and the third transmission gear and the fourth transmission gear are meshed for transmission.
Further, the hybrid aeroengine with the double motors comprises an intermediate casing and a first bracket, wherein the first bracket is fixedly connected with the intermediate casing, and the first motor is arranged on the first bracket.
Further, the hybrid aeroengine with the double motors comprises an intermediate casing and a second bracket, the second bracket is fixedly connected with the intermediate casing, and the second motor is arranged on the first bracket and the second bracket.
Further, the hybrid aeroengine with the double motors comprises an outer culvert casing, and the energy storage battery pack is fixed on the outer side of the outer culvert casing.
Further, the hybrid aeroengine with the double motors comprises an electric fuel accessory which is arranged on the outer side of the outer culvert casing and is connected with the energy storage battery pack.
Further, the hybrid aeroengine with the double motors comprises an electric lubricating oil accessory which is arranged on the outer side of the outer culvert casing and connected with the energy storage battery pack.
Compared with the prior art, the beneficial effects that above-mentioned at least one technical scheme that this description embodiment adopted can reach include at least: according to the invention, four working modes can be switched by additionally arranging the first motor and the second motor, so that the core machine works in a high-efficiency state for a long time, and the working efficiency of the engine is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic structural view of an embodiment of the present invention.
Reference numerals in the drawings: 1. an air intake device; 3. a fan rotor; 4. a second motor; 5. a first motor; 6. an intermediate case; 7. a compressor; 8. an outer culvert casing; 9. a main combustion chamber; 10. a high pressure turbine; 11. a rear bearing casing; 12. an connotation force transmission device; 13. an external culvert exhaust device; 15. an energy storage battery pack; 16. an electric fuel accessory; 17. an electric lubricating oil accessory; 18. a high pressure shaft; 19. a fan shaft; 61. a first bracket; 62. a second bracket; 51. a first transmission gear; 52. a second transmission gear; 41. a fourth transmission gear; 42. and a third transmission gear.
Detailed Description
Embodiments of the present application are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
As shown in fig. 1, an embodiment of the present invention provides a hybrid aero-engine with dual motors, comprising a core engine, a first motor 5, a fan shaft 19 and a second motor 4. The core machine has a high pressure shaft 18; the first motor 5 is connected with the high-voltage shaft 18, the first motor 5 has a first working mode and a second working mode, the first motor 5 can drive the high-voltage shaft 18 to rotate in the first working mode, and the high-voltage shaft 18 can drive the first motor 5 to rotate to generate electricity in the second working mode; the fan shaft 19 is arranged at a distance from the high-pressure shaft 18 and is positioned at an upstream position of the high-pressure shaft 18; the second motor 4 is connected to the fan shaft 19, and the second motor 4 has a third operation mode in which the second motor 4 can drive the fan shaft 19 to rotate, and a fourth operation mode in which the fan shaft 19 can drive the second motor 4 to rotate to generate electricity.
According to the invention, four working modes can be switched by additionally arranging the first motor 5 and the second motor 4, so that the core machine works in a high-efficiency state for a long time, and the working efficiency of the engine is improved.
In the embodiment of the invention, the stator and the rotor of the first motor 5 and the second motor 4 can be cooled by introducing lubricating oil from the outside of the engine, entering the inside of the motor through the intermediate casing 6, and then being discharged through an engine intermediate casing lubricating oil return pipeline.
The hybrid aeroengine with double motors further comprises an energy storage battery pack 15, and the first motor 5 and the second motor 4 are connected with the energy storage battery pack 15. The provision of the energy storage battery 15 can be used to store the electrical energy generated by the first electric machine 5 and the second electric machine 4 and to supply it to the electrical components of the aircraft engine or of the aircraft.
The energy storage battery pack 15 transmits electric energy to the second motor 4 through the transmission cable, so that the second motor 4 rotates, and the fan rotor 3 is driven to rotate, and compression work is done on air flow. The first motor 5 can adjust its output power through the engine control system, adjust its output rotation speed, realize fan operating condition adjustment.
The fan rotor 3 is supported on the air intake device 1 and the intermediate case 6 by a roller bearing and a ball bearing, respectively. The axial load of the fan rotor 3 is transmitted outward through the intermediate casing 6, and the radial load is transmitted outward through the intake device 1 and the intermediate casing 6, respectively.
The high-voltage shaft 18 is provided with a first transmission gear 51, the first motor 5 is provided with a second transmission gear 52, and the first transmission gear 51 and the second transmission gear 52 are meshed for transmission. The fan shaft 19 is provided with a third transmission gear 42, the second motor 4 is provided with a fourth transmission gear 41, and the third transmission gear 42 and the fourth transmission gear 41 are meshed for transmission.
The compressor 7 and the high-pressure turbine 10 are connected into a shaft, a first transmission gear 51 is arranged at the front section of the shaft, the first transmission gear 51 drives a second transmission gear 52 to rotate, the second transmission gear 52 drives the first motor 5 to rotate to generate electric energy, and the generated electric energy is transmitted to the energy storage battery 15 through a transmission cable and stored in the energy storage battery 15. Wherein the first electric machine 5 can adjust its generated power by the engine control system, thereby adjusting the amount of power it extracts from the core machine.
As shown in fig. 1, the dual-motor hybrid aeroengine in the embodiment of the present invention includes an intermediate casing 6, a first bracket 61 and a second bracket 62, the first bracket 61 is fixedly connected with the intermediate casing 6, and the first motor 5 is mounted on the first bracket 61. The second bracket 62 is fixedly connected with the intermediate casing 6, and the second motor 4 is mounted on the second bracket 62.
The core unit body formed by the intermediate casing 6, the compressor 7, the main combustion chamber 9 and the high-pressure turbine 10 can be selected from a core unit body of a conventional turbojet/turbofan engine, and can also be selected from a verified test core machine.
The double-motor hybrid aeroengine in the embodiment of the invention comprises an outer culvert casing 8, and an energy storage battery pack 15 is fixed on the outer side of the outer culvert casing 8.
The hybrid aeroengine with double motors comprises an electric fuel accessory 16 and an electric lubricating oil accessory 17, wherein the electric fuel accessory 16 is arranged outside the outer culvert casing 8 and is connected with the energy storage battery pack 15. The electric lubricating oil accessory 17 is arranged outside the outer culvert casing 8 and is connected with the energy storage battery pack 15.
The driving of the electric fuel accessory 16 and the electric lubricant accessory 17 is driven by the electric energy transmitted by the energy storage battery pack 15 through the transmission cable. The electric fuel accessory 16 outputs fuel required for engine operation, and the electric lubricant accessory 17 pressurizes lubricant of an engine lubricant system.
When in operation, the device comprises:
the air inlet device 1 introduces an air flow into the engine, and after the air flow is compressed by the fan rotor 3, the air flow is divided into two air flows in the intermediate case 6 and respectively enters the outer culvert passage and the inner culvert passage; the air flow in the connotation passage is compressed by the air compressor 7, the compressed air flow enters the main combustion chamber 9 to be mixed with fuel oil for combustion, the mixed air flow after combustion enters the high-pressure turbine 10 to expand and do work, and the air flow after expansion and doing work enters the connotation force transmission device 12 to expand and accelerate and then is discharged into the atmosphere to generate thrust; the air flow entering the outer culvert passage is expanded and accelerated in the outer culvert exhaust device 13 and then discharged into the atmosphere to generate thrust.
The invention has the following working modes:
in the pure electric mode, the energy storage battery pack 15 supplies power to the first motor 5 and drives the second transmission gear 52 to rotate, so that the fan rotor 3 is driven to rotate, no fuel is injected into the main combustion chamber 9, and the core machine is in a windmill state. The pure electric mode is mainly used for the low thrust requirement state of the aircraft, such as the working conditions of ground slow running, ground sliding, high altitude small meter number and the like.
In the series mode, the core machine works at full rotation speed, and the power of the core machine is mainly used for driving the first motor 5 to generate power by increasing the power generation power of the first motor 5, so that the thrust required by the aircraft is mainly generated by the air flow of the external culvert passage. The series mode is mainly used for the cruise state of the aircraft or the state of insufficient electric quantity of the energy storage battery pack 15, and ensures the long-time stable operation of the aircraft.
In the parallel mode, the core machine works at the full rotation speed, the generated power of the first motor 5 is adjusted to be in a proper state, and the thrust required by the aircraft is generated by the inner culvert passage airflow and the outer culvert passage airflow together. The parallel mode is mainly used for high thrust demand states of the aircraft, such as climbing and accelerating lamp working conditions.
The kinetic energy recovery mode, the engine is in windmill mode, the first motor 5 and the second motor 4 are both in power generation state, and the energy storage battery pack 15 is charged. The kinetic energy recovery mode is mainly used for the windmills or landing states of the aircraft.
The above operation modes are by a combination of the above first operation mode, second operation mode, third operation mode and fourth operation mode.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. A dual-motor hybrid aircraft engine, comprising:
a core machine having a high pressure shaft (18);
the first motor (5) is connected with the high-voltage shaft (18), the first motor (5) is provided with a first working mode and a second working mode, the first motor (5) can drive the high-voltage shaft (18) to rotate in the first working mode, and the high-voltage shaft (18) can drive the first motor (5) to rotate to generate electricity in the second working mode;
a fan shaft (19) which is disposed at a distance from the high-pressure shaft (18) and is located at a position upstream of the high-pressure shaft (18);
the second motor (4) is connected with the fan shaft (19), the second motor (4) is provided with a third working mode and a fourth working mode, the second motor (4) can drive the fan shaft (19) to rotate in the third working mode, and the fan shaft (19) can drive the second motor (4) to rotate to generate electricity in the fourth working mode.
2. The dual-motor hybrid aircraft engine according to claim 1, further comprising an energy storage battery (15), wherein the first motor (5) and the second motor (4) are both connected to the energy storage battery (15).
3. The dual-motor hybrid aeroengine according to claim 1, wherein a first transmission gear (51) is provided on the high-voltage shaft (18), a second transmission gear (52) is provided on the first motor (5), and the first transmission gear (51) and the second transmission gear (52) are in meshed transmission.
4. A hybrid aeroengine with double electric machines according to claim 1, characterised in that the fan shaft (19) is provided with a third transmission gear (42), the second electric machine (4) is provided with a fourth transmission gear (41), and the third transmission gear (42) and the fourth transmission gear (41) are in meshing transmission.
5. The dual-motor hybrid aircraft engine according to claim 1, characterized in that it comprises an intermediate casing (6) and a first bracket (61), the first bracket (61) being fixedly connected to the intermediate casing (6), the first motor (5) being mounted on the first bracket (61).
6. The dual-motor hybrid aircraft engine according to claim 1, characterized in that it comprises an intermediate casing (6) and a second bracket (62), the second bracket (62) being fixedly connected to the intermediate casing (6), the second motor (4) being mounted on the second bracket (62).
7. The dual-motor hybrid aeroengine as claimed in claim 2, wherein the dual-motor hybrid aeroengine comprises an outer culvert casing (8), and the energy storage battery pack (15) is fixed outside the outer culvert casing (8).
8. The dual-motor hybrid aircraft engine according to claim 7, characterized in that it comprises an electric fuel accessory (16) arranged outside the outer casing (8) and connected with the energy storage battery (15).
9. The dual-motor hybrid aircraft engine according to claim 7, characterized in that it comprises an electric lubricating oil accessory (17) arranged outside the outer box (8) and connected with the energy storage battery (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410123019.9A CN117644979A (en) | 2024-01-30 | 2024-01-30 | Double-motor hybrid aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410123019.9A CN117644979A (en) | 2024-01-30 | 2024-01-30 | Double-motor hybrid aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117644979A true CN117644979A (en) | 2024-03-05 |
Family
ID=90045491
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410123019.9A Pending CN117644979A (en) | 2024-01-30 | 2024-01-30 | Double-motor hybrid aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117644979A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3130783A1 (en) * | 2015-08-14 | 2017-02-15 | General Electric Company | Gas turbine engine stall margin management |
| CN108252807A (en) * | 2016-12-28 | 2018-07-06 | 中国航发商用航空发动机有限责任公司 | The DYN dynamic engine propulsion system of turbine |
| CN109018380A (en) * | 2017-06-08 | 2018-12-18 | 通用电气公司 | Hybrid electric propulsion system and operating method for aircraft |
| US20180372588A1 (en) * | 2017-06-23 | 2018-12-27 | General Electric Company | Propulsion system for an aircraft |
| CN110397519A (en) * | 2019-08-02 | 2019-11-01 | 绵阳小巨人动力设备有限公司 | A kind of miniature oil electric mixed dynamic fanjet |
| CN111699311A (en) * | 2018-02-09 | 2020-09-22 | 赛峰集团 | Hybrid propulsion for aircraft |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
-
2024
- 2024-01-30 CN CN202410123019.9A patent/CN117644979A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3130783A1 (en) * | 2015-08-14 | 2017-02-15 | General Electric Company | Gas turbine engine stall margin management |
| CN108252807A (en) * | 2016-12-28 | 2018-07-06 | 中国航发商用航空发动机有限责任公司 | The DYN dynamic engine propulsion system of turbine |
| CN109018380A (en) * | 2017-06-08 | 2018-12-18 | 通用电气公司 | Hybrid electric propulsion system and operating method for aircraft |
| US20180372588A1 (en) * | 2017-06-23 | 2018-12-27 | General Electric Company | Propulsion system for an aircraft |
| CN111699311A (en) * | 2018-02-09 | 2020-09-22 | 赛峰集团 | Hybrid propulsion for aircraft |
| CN110397519A (en) * | 2019-08-02 | 2019-11-01 | 绵阳小巨人动力设备有限公司 | A kind of miniature oil electric mixed dynamic fanjet |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
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