CN104393673A - Power supply system for electronic controller of aircraft engine - Google Patents
Power supply system for electronic controller of aircraft engine Download PDFInfo
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- CN104393673A CN104393673A CN201410713720.2A CN201410713720A CN104393673A CN 104393673 A CN104393673 A CN 104393673A CN 201410713720 A CN201410713720 A CN 201410713720A CN 104393673 A CN104393673 A CN 104393673A
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- electronic controller
- power supply
- generator
- airborne vehicle
- aeroengine
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- 238000004804 winding Methods 0.000 claims description 22
- 238000000034 method Methods 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000009466 transformation Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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Abstract
The invention provides a power supply system for an electronic controller of an aircraft engine. The electronic controller comprises a plurality of work channels being independent to each other, comprises an electric generator, an aircraft power supply and a power source selecting module mounted on the circuit board of each work channel of the electronic controller; the electric generator is connected to each power source selecting module, the electric generator is driven by the aircraft engine for offering the power for different work channels of the electronic controller, the aircraft power supply is connected with each power source selecting module; the main power supply of each work channel of the electronic controller is switched between the electric generator and the aircraft power supply through the internal power source selecting module. The aircraft power supply is matched with the electric generator for guaranteeing stable power source for the electronic controller while any device has the fault.
Description
Technical field
The present invention relates to aviation control appliance Power Management Design field, more specifically, relate to a kind of aeroengine electronic controller electric power system.
Background technology
The supply power mode of the electronic controller of existing aero-engine adopts airborne vehicle power supply to provide mostly, along with the development of generator techniques, has occurred the mode driving generator to power to electronic controller by aero-engine.Domestic aero-engine is all adopt single pass supply power mode mostly, and generator does not possess anti-short circuit capability, makes electronic controller comparatively responsive to power quality, and fail safe, the reliability of engine operation are low.
Summary of the invention
The present invention is for overcoming at least one defect described in above-mentioned prior art, and providing a kind of can provide safety and stability power supply again can the electric power system of energy savings to aeroengine electronic controller.
Another object of the present invention is the architecting method providing a kind of aeroengine electronic controller electric power system.
In order to reach above-mentioned technical purpose, technical scheme of the present invention is as follows:
A kind of aeroengine electronic controller electric power system, this electronic controller comprises some separate service aisles, comprises generator, airborne vehicle power supply and is arranged on the power supply selection module on each service aisle circuit board of electronic controller; Described generator and each power supply select module to be connected, and generator is driven by aero-engine and powers to the different operating passage of electronic controller, and airborne vehicle power supply and each power supply select module to be connected; The main power source supply of each service aisle of electronic controller selects module to switch between generator and airborne vehicle power supply by the power supply of its inside.
Further, generator is installed on the transmission casing of aero-engine, is driven by the Accessory Gear Box in transmission casing.
In the present invention, by generator and airborne vehicle power supply are cooperated use, power supply in electronic controller is utilized to select module to switch generator or the airborne vehicle power supply main power source as electronic controller, after arbitrary unit breaks down, another still can realize separately full-amount power supply supply, and generator utilizes the principle that the kinetic transformation of airborne vehicle self engine is electric energy, delayed the consumption of airborne vehicle electric energy.
Further, described generator comprises armature winding the same number of with electronic controller supplying channels, and generator powers to this electronic controller independently of each other by armature winding.
In the present invention, generator is provided with some armature winding to connect the some service aisles of electronic controller, independently of each other electronic controller is powered, the power supply supply of other windings to electronic controller can not be affected when arbitrary winding damages, guarantee the power supply supply stability of electronic controller.
Preferably, in order to make armature winding possess anti-short circuit capability, described armature winding is manufactured by Short Circuit withstand material.
Preferably, described generator is alternating current generator.
An architecting method for aeroengine electronic controller electric power system, comprises the following steps:
S1: in Aero-Engine Start process, airborne vehicle power supply is powered to the some passages of electronic controller, and generator is not powered to electronic controller;
S2: when engine speed reaches threshold values θ, the power supply in each service aisle of electronic controller selects module to be switched to the main power source of generator as electronic controller, and airborne vehicle power supply stops powering to electronic controller;
S3: in flight course, when generator failure cannot supplying power for outside time, power supply in each service aisle of electronic controller selects module to be switched to the main power source of airborne vehicle as electronic controller.
Preferably, described θ is 3288 rev/min.
Compared with prior art, the beneficial effect of technical solution of the present invention is:
1, by airborne vehicle power supply and generator are cooperated use, when ensureing that arbitrary equipment breaks down wherein, electronic controller has stable power supply supply;
2, be provided with separate the powering to electronic controller of many group armature winding in generator, arbitrary winding breaks down also can not affect other windings independently to the power supply supply of electronic controller;
3, kinetic transformation is electric energy by generator, and powering to electronic controller with regard to independent when generator speed reaches threshold values, without the need to consuming the power supply of airborne vehicle self again, is airborne vehicle energy savings.
Accompanying drawing explanation
Fig. 1 is 1 work structuring schematic diagram of the present invention in embodiment.
Embodiment
Accompanying drawing, only for exemplary illustration, can not be interpreted as the restriction to this patent;
In order to better the present embodiment is described, some parts of accompanying drawing have omission, zoom in or out, and do not represent the size of actual product;
To those skilled in the art, in accompanying drawing, some known features and explanation thereof may be omitted is understandable.
Below in conjunction with drawings and Examples, technical scheme of the present invention is described further.
embodiment 1
As shown in Figure 1, a kind of aeroengine electronic controller electric power system, this electronic controller comprises some separate service aisles, comprises generator, airborne vehicle power supply and is arranged on the power supply selection module on each service aisle circuit board of electronic controller; Described generator and each power supply select module to be connected, and generator is driven by aero-engine and powers to the different operating passage of electronic controller, and airborne vehicle power supply and each power supply select module to be connected; The main power source supply of each service aisle of electronic controller selects module to switch between generator and airborne vehicle power supply by the power supply of its inside.
In the present embodiment, the some separate passages of aeroengine electronic controller design, the corresponding armature winding comprising some numbers of generator, independently of each other each passage is powered, the supplying channels that electronic controller has T, D two groups separate, generating inside is provided with two groups of armature winding and powers to T, D two passages respectively, armature winding 1 pair of T passage is powered, armature winding 2 pairs of D passages are powered, can not interact when armature winding 1 or any one damage of armature winding 2, guarantee the stability that electronic controller power supply is supplied.
Having installed power supply in T, D passage of electronic controller respectively selects module 1 and power supply to select module 2, and the main supply power supply that power supply selects module 1,2 to allow electronic controller T, D make passage respectively freely switches between generator and airborne vehicle power supply.
In the present embodiment, armature winding possesses anti-short circuit capability, when winding two-phase or three phase faults, alternating current generator can not be caused to damage, and airborne vehicle power supply exports 28V direct current.
embodiment 2
A control method for aeroengine electronic controller electric power system, process is as follows:
S1: in Aero-Engine Start process, airborne vehicle power supply is powered to the some passages of electronic controller, and generator is not powered to electronic controller;
S2: when engine speed reaches threshold values θ, the power supply in each service aisle of electronic controller selects module to be switched to the main power source of generator as electronic controller, and airborne vehicle power supply stops powering to electronic controller;
S3: in flight course, when generator failure cannot supplying power for outside time, power supply in each service aisle of electronic controller selects module to be switched to the main power source of airborne vehicle as electronic controller.
In the present embodiment, θ is 3288 rev/min, when the rotating speed of aircraft engine reaches more than 3288 rev/min just can drive electrical generators send the voltage meeting Electronic Control and normally run, now electronic controller is only by generator powered, when all armature winding of generator all cannot supplying power for outside time, airborne vehicle Power supply can be automatically switched to again, ensure that electronically controlled stable power supply supply.
The corresponding same or analogous parts of same or analogous label;
Describe in accompanying drawing position relationship for only for exemplary illustration, the restriction to this patent can not be interpreted as;
Obviously, the above embodiment of the present invention is only for example of the present invention is clearly described, and is not the restriction to embodiments of the present invention.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all execution modes.All any amendments done within the spirit and principles in the present invention, equivalent to replace and improvement etc., within the protection range that all should be included in the claims in the present invention.
Claims (7)
1. an aeroengine electronic controller electric power system, this electronic controller comprises some separate service aisles, it is characterized in that, comprise generator, airborne vehicle power supply and be arranged on the power supply selection module on each service aisle circuit board of electronic controller; Described generator and each power supply select module to be connected, and generator is driven by aero-engine and powers to the different operating passage of electronic controller, and airborne vehicle power supply and each power supply select module to be connected; The main power source supply of each service aisle of electronic controller selects module to switch between generator and airborne vehicle power supply by the power supply of its inside.
2. aeroengine electronic controller electric power system according to claim 1, is characterized in that, described generator is installed on the transmission casing of aero-engine, is driven by the Accessory Gear Box in transmission casing.
3. aeroengine electronic controller electric power system according to claim 1, it is characterized in that, described generator comprises armature winding the same number of with electronic controller supplying channels, and generator powers to this electronic controller independently of each other by armature winding.
4. aeroengine electronic controller electric power system according to claim 2, is characterized in that, described armature winding is manufactured by Short Circuit withstand material.
5. aeroengine electronic controller electric power system according to claim 1, is characterized in that, described generator is alternating current generator.
6. a control method for the aeroengine electronic controller electric power system as described in any one of claim 1-5, is characterized in that, comprise the following steps:
S1: in Aero-Engine Start process, airborne vehicle power supply is powered to the some passages of electronic controller, and generator is not powered to electronic controller;
S2: when engine speed reaches threshold values θ, the power supply in each service aisle of electronic controller selects module to be switched to the main power source of generator as electronic controller, and airborne vehicle power supply stops powering to electronic controller;
S3: in flight course, when generator failure cannot supplying power for outside time, power supply in each service aisle of electronic controller selects module to be switched to the main power source of airborne vehicle as electronic controller.
7. aeroengine electronic controller electric power system according to claim 6, is characterized in that, described θ is 3288 rev/min.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410713720.2A CN104393673A (en) | 2014-12-02 | 2014-12-02 | Power supply system for electronic controller of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410713720.2A CN104393673A (en) | 2014-12-02 | 2014-12-02 | Power supply system for electronic controller of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104393673A true CN104393673A (en) | 2015-03-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410713720.2A Pending CN104393673A (en) | 2014-12-02 | 2014-12-02 | Power supply system for electronic controller of aircraft engine |
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| Country | Link |
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| CN (1) | CN104393673A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070257558A1 (en) * | 2006-05-05 | 2007-11-08 | Hispano Suiza | Electrical power supply arrangement for an aircraft |
| CN201789331U (en) * | 2010-08-06 | 2011-04-06 | 四川长虹电器股份有限公司 | Aircraft engine power system |
| CN103116320A (en) * | 2011-11-17 | 2013-05-22 | 中航商用航空发动机有限责任公司 | Distributed type aero-engine full authority digital engine control (FADEC) system |
| CN103414243A (en) * | 2013-08-22 | 2013-11-27 | 中国航空动力机械研究所 | Power supply system of electronic engine controller |
-
2014
- 2014-12-02 CN CN201410713720.2A patent/CN104393673A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070257558A1 (en) * | 2006-05-05 | 2007-11-08 | Hispano Suiza | Electrical power supply arrangement for an aircraft |
| CN201789331U (en) * | 2010-08-06 | 2011-04-06 | 四川长虹电器股份有限公司 | Aircraft engine power system |
| CN103116320A (en) * | 2011-11-17 | 2013-05-22 | 中航商用航空发动机有限责任公司 | Distributed type aero-engine full authority digital engine control (FADEC) system |
| CN103414243A (en) * | 2013-08-22 | 2013-11-27 | 中国航空动力机械研究所 | Power supply system of electronic engine controller |
Non-Patent Citations (2)
| Title |
|---|
| 姚华: "《航空发动机全权限数字电子控制系统》", 30 June 2014 * |
| 胡世民等: "《民航发动机控制》", 31 January 2000 * |
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Application publication date: 20150304 |