CN110761849A - Fan assembly with built-in generator - Google Patents
Fan assembly with built-in generator Download PDFInfo
- Publication number
- CN110761849A CN110761849A CN201911148422.2A CN201911148422A CN110761849A CN 110761849 A CN110761849 A CN 110761849A CN 201911148422 A CN201911148422 A CN 201911148422A CN 110761849 A CN110761849 A CN 110761849A
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- China
- Prior art keywords
- fan
- air inlet
- rotor
- generator
- built
- Prior art date
- 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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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention belongs to the structural design scheme of an aircraft engine, and relates to a fan assembly with a built-in generator, which consists of a fan rotor, a transfer shaft, an air inlet support plate, an air inlet cone, a motor and a bearing; the fan rotor is a part of an engine and rotates at a high speed, the front end of the fan rotor is connected with the adapter shaft, the adapter shaft is provided with the motor rotor, and the fan rotor drives the motor rotor to rotate through the adapter shaft; the air inlet support plate is arranged on a fan casing, the fan casing is connected with a supporting casing, and the fan casing and the supporting casing are self force transmission parts of the engine. The air inlet cone is arranged on the air inlet support plate and is a static part, a sealing structure is arranged at the connecting position of the air inlet cone and the rotor, and the motor stator and a bearing for supporting the motor rotor are fixedly arranged on the air inlet cone. The structure provided by the invention can improve the power supply capacity of the engine, reduce the weight of the engine, and is convenient to install and easy to maintain the built-in motor.
Description
Technical Field
The invention relates to an aircraft engine fan assembly, in particular to a fan assembly with a built-in generator.
Background
With the increase of power-consuming accessories such as airborne radars, sensors, weapons and the like of the airplane, the power requirement of the airplane on the power supply of an engine is higher and higher, and the power obtained by outputting the power through a route of a high-voltage rotor, a central transmission device, an engine accessory case, an airplane accessory case and a generator is not enough to meet the power requirement of the airplane. In order to further increase the power supply capacity of the engine and meet the fighting requirements of the aircraft, a scheme for extracting power by a built-in generator in a fan of the aircraft engine is provided.
Although the mechanical transmission power output mode adopted on the high-pressure rotor is mature and widely applied, a set of complex and heavy transmission device is needed, if the low-pressure rotor adopts the mechanical transmission mode to output power, the weight burden of the engine is greater than the power output benefit, and the motor is arranged in the inner cavity of the fan of the engine to extract power, so that the weight advantage is achieved. The development and application conditions of a built-in generator of a fan of a double-rotor turbofan engine are not existed in China.
Disclosure of Invention
The purpose of the invention is: the problem that the output power efficiency is low and the additional weight is large in the existing mechanical transmission mode is solved, the fan assembly with the built-in generator is provided, power extraction is carried out on the low-voltage rotor, and the increase of the power supply capacity of the engine is achieved.
The technical solution of the invention is as follows: a fan assembly with a built-in generator is composed of a fan rotor, a rotary shaft, an air inlet support plate, an air inlet cone, a motor and a bearing; the fan rotor is a part of an engine and rotates at a high speed, the front end of the fan rotor is connected with the adapter shaft, the adapter shaft is provided with the motor rotor, and the fan rotor drives the motor rotor to rotate through the adapter shaft; the air inlet support plate is arranged on a fan casing, the fan casing is connected with a supporting casing, and the fan casing and the supporting casing are self force transmission parts of the engine. The air inlet cone is arranged on the air inlet support plate and is a static part, a sealing structure is arranged at the connecting position of the air inlet cone and the rotor, and the motor stator and a bearing for supporting the motor rotor are fixedly arranged on the air inlet cone.
Preferably, the air inlet support plate is of a hollow structure, and motor accessory parts and wire penetration can be placed in the air inlet support plate.
The beneficial technical effects are that: the invention provides a scheme for extracting power of a double-rotor turbofan engine, and the power supply capacity of the engine can be improved by extracting the power of a low-voltage rotor through a built-in electrically-excited double-salient motor of a fan. Compared with the traditional mechanical transmission scheme, the generator has the advantage of weight reduction in extracting the rotor power, and the built-in electro-magnetic doubly salient motor has the effects of convenience in installation and easiness in maintenance.
Drawings
FIG. 1 is a schematic structural view of the present invention;
in the figure, 1-fan rotor, 2-transfer shaft, 3-air inlet support plate, 4-air inlet cone, 5-motor rotor, 6-motor stator and 7-bearing.
Detailed Description
The present invention provides a fan assembly of a built-in generator, which is described in detail below by taking a built-in electric excitation doubly salient generator as an example, as shown in fig. 1, the scheme of the built-in electric excitation doubly salient generator of the fan of the double-rotor turbofan engine is used for mounting electric excitation doubly salient motors 4 and 5 in cavities of the fan 1 and an air inlet cone 4 for low-voltage rotor power extraction, wherein a motor rotor 5 is mounted on a fan shaft 2, and a motor stator is mounted on the air inlet cone 4 and fixed by an air inlet support plate. When the low-voltage rotor of the double-rotor turbofan engine rotates, the motor rotor 4 is rotated, and the motor rotor 4 and the motor stator 5 cut magnetic induction lines to generate electric energy. In order to realize the scheme of embedding the electric excitation doubly salient generators 4 and 5 in the fan 1, the design method can be used for further carrying out adaptive improvement, and the method specifically comprises the following steps:
and determining the form of the fan air inlet support plate according to the structural form of the engine fan rotor. And if the fan supporting mode is changed, the dynamic characteristic analysis of the rotor is carried out again, the fulcrum oil supply structure is redesigned, and the force transmission calculation of the whole machine is carried out again. If the fan is provided with an air inlet support plate in front, the size of an inner cavity of an air inlet cone on the support plate is adjusted, and a fulcrum oil supply structure is improved.
Designing an air inlet support plate 1; according to whether the supporting position needs lubrication and supporting rigidity, the structural size and the number of the air inlet support plates 3 are analyzed, the dynamic characteristics of the rotor of the fan 1 with the motor rotor 5 are analyzed, and the supporting point position is designed under the condition that the dynamic characteristics meet the requirements.
After the position of the air inlet support plate 3 is determined, the air inlet support plate and the air inlet cone 4 are combined to optimize a flow passage surface, so that the air inlet flow and the pneumatic loss of the fan are reduced to the optimal state.
The motor with proper power is selected, and a split type brushless motor can be selected. The generator can also be an electrically excited double salient pole generator. The electric excitation double salient pole generator has no brush and commutator, and no winding on the rotor, and has no need of position sensor and controllable power converter, so that it is suitable for rotating machine of aeroengine with strict requirement for rotor balance. The size of the rotor of the generator is given according to the space in the fan, and the power of the generator with large volume is also large.
The motor rotor is arranged on the transfer shaft. The generator is fixed on the fan shaft in a mechanical connection mode, and a rotor shaft of the generator is connected to the fan shaft through a flange mounting edge or sleeved on the fan shaft.
The fan rotor is a rotating part, the air inlet cone is a static part, and in order to ensure that the pressure of the inner cavity of the fan is in a design range, a sealing device, namely finger type sealing and comb tooth sealing, is arranged at the connecting position of the fan rotor and the air inlet cone. In order to ensure the lubricating requirement of the bearing during operation, an oil inlet pipeline and an oil return pipeline which are penetrated and led by an air inlet support plate are separately arranged.
Claims (10)
1. A fan assembly with a built-in generator, comprising: the fan assembly consists of a fan casing, a fan stator, a fan rotor, a rotary shaft, an air inlet support plate, an air inlet cone, a generator and a bearing; the fan casing, the fan stator and the fan rotor are self parts of the engine; the fan rotor is a part rotating at high speed, the front end of the fan rotor is connected with the adapter shaft, the motor rotor is arranged on the adapter shaft, and the fan rotor drives the motor rotor to rotate through the adapter shaft; the air inlet support plate is arranged on the fan casing, the fan casing is connected with the supporting casing, and the fan casing and the supporting casing are self force transmission parts of the engine; the air inlet cone is arranged on the air inlet support plate and is a static part, a sealing structure is arranged at the connecting position of the air inlet cone and the rotor, and the generator stator and a bearing for supporting the generator rotor are fixedly arranged on the air inlet cone.
2. The fan assembly with built-in generator as claimed in claim 1, wherein: the air inlet support plate is of a hollow structure.
3. The fan assembly of a built-in generator according to claim 1 or 2, wherein: the form of the inlet strut may be modified.
4. The fan assembly with built-in generator as claimed in claim 1, wherein: the generator adopts a brushless motor.
5. The fan assembly with built-in generator as claimed in claim 4, wherein: the brushless motor adopts an electro-magnetic doubly salient generator.
6. The fan assembly with built-in generator as claimed in claim 1, wherein: the motor is fixed on the fan shaft in a mechanical connection mode.
7. The fan assembly of an internal generator according to claim 6, wherein: the rotor of the motor is connected to the fan shaft through the flange mounting edge or sleeved on the fan shaft.
8. The fan assembly with built-in generator as claimed in claim 1, wherein: the sealing structure adopts finger type sealing or labyrinth sealing.
9. The fan assembly with built-in generator as claimed in claim 1, wherein: and the air inlet support plate is provided with an air inlet pipeline and an oil return pipeline.
10. The fan assembly of an internal generator according to claim 9, wherein: and a lubricating nozzle is arranged at the position of the bearing in the air inlet cone, and the lubricating nozzle is communicated with an oil inlet pipeline to provide cooling and lubrication for the bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911148422.2A CN110761849A (en) | 2019-11-21 | 2019-11-21 | Fan assembly with built-in generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911148422.2A CN110761849A (en) | 2019-11-21 | 2019-11-21 | Fan assembly with built-in generator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110761849A true CN110761849A (en) | 2020-02-07 |
Family
ID=69339019
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911148422.2A Pending CN110761849A (en) | 2019-11-21 | 2019-11-21 | Fan assembly with built-in generator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110761849A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112049909A (en) * | 2020-09-07 | 2020-12-08 | 中国航发贵阳发动机设计研究所 | Power generation system with stepless speed change device |
| CN112628208A (en) * | 2020-12-23 | 2021-04-09 | 中国航发沈阳发动机研究所 | Air entraining structure of air compressor |
| CN116906182A (en) * | 2023-09-13 | 2023-10-20 | 中国航发沈阳发动机研究所 | Local balanced structure of aeroengine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040255590A1 (en) * | 2003-06-23 | 2004-12-23 | Pratt & Whiney Canada Corp. | Differential geared turbine engine with torque modulation capability |
| CN101205835A (en) * | 2006-12-21 | 2008-06-25 | 通用电气公司 | Integrated boost cavity ring generator for turbofan and turboshaft engines |
| EP2141339A1 (en) * | 2008-07-03 | 2010-01-06 | Rolls-Royce Deutschland Ltd & Co KG | Turbofan engine with at least one device for driving at least one generator |
| CN102562318A (en) * | 2010-12-29 | 2012-07-11 | 通用电气航空系统有限责任公司 | Method and system for powering a vehicle |
-
2019
- 2019-11-21 CN CN201911148422.2A patent/CN110761849A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040255590A1 (en) * | 2003-06-23 | 2004-12-23 | Pratt & Whiney Canada Corp. | Differential geared turbine engine with torque modulation capability |
| CN101205835A (en) * | 2006-12-21 | 2008-06-25 | 通用电气公司 | Integrated boost cavity ring generator for turbofan and turboshaft engines |
| EP2141339A1 (en) * | 2008-07-03 | 2010-01-06 | Rolls-Royce Deutschland Ltd & Co KG | Turbofan engine with at least one device for driving at least one generator |
| CN102562318A (en) * | 2010-12-29 | 2012-07-11 | 通用电气航空系统有限责任公司 | Method and system for powering a vehicle |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112049909A (en) * | 2020-09-07 | 2020-12-08 | 中国航发贵阳发动机设计研究所 | Power generation system with stepless speed change device |
| CN112628208A (en) * | 2020-12-23 | 2021-04-09 | 中国航发沈阳发动机研究所 | Air entraining structure of air compressor |
| CN116906182A (en) * | 2023-09-13 | 2023-10-20 | 中国航发沈阳发动机研究所 | Local balanced structure of aeroengine |
| CN116906182B (en) * | 2023-09-13 | 2023-12-15 | 中国航发沈阳发动机研究所 | Local balanced structure of aeroengine |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200207 |
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| RJ01 | Rejection of invention patent application after publication |