CN102664577A - High-power-factor and high-reliability power supply dedicated for aeroengine - Google Patents
High-power-factor and high-reliability power supply dedicated for aeroengine Download PDFInfo
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- CN102664577A CN102664577A CN2012101314257A CN201210131425A CN102664577A CN 102664577 A CN102664577 A CN 102664577A CN 2012101314257 A CN2012101314257 A CN 2012101314257A CN 201210131425 A CN201210131425 A CN 201210131425A CN 102664577 A CN102664577 A CN 102664577A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to a power supply dedicated for an aeroengine, and the power supply consists of a permanent-magnet alternating current generator and a DC/DC (Direct Current to Direct Current) converter. According to the power supply, a dual-pair-pole permanent-magnet motor is adopted based on the traditional permanent-magnet synchronous generator so as to realize two three-phase outputs, and two armature windings are almost independent in magnetic circuits, and the other three-phase output can normally work when one three-phase output is in short-circuit; the reliable fault tolerance function is realized, and the structure is simple; aiming at the characteristic of large change range of rotating speed of the engine, the DC/DC converter adopts a two-stage conversion scheme, a front stage is a three-phase half-controlled rectifier, and a rear stage is a BUCK converter; when the rotating speed of the engine is relatively low, the output power factor of the engine is increased through the three-phase half-controlled rectifier; when the rotating speed of the engine is relatively high, a power tube is switched off, so that the front stage works at a three-phase full-bridge rectification state; the rear stage realizes the stability of an output voltage; and when the rotating speed is relatively low, the front stage works at a BOOST state, and the self inductance of the armature windings of the generator is used as electrical inductance, so that the volume and the weight of the system are reduced.
Description
Technical field
The present invention relates to a kind of aircraft engine special power-supply system, belong to Technics of Power Electronic Conversion technology and electrical equipment and electrical technology in the electrical technology subject.
Background technology
The special power-supply system of aero-engine is made up of magneto alternator, rectifier bridge and DC/DC converter; Require special power-supply system can supply power to engine controller at engine speed change scope 15%-115%; And only supply power to engine controller; Do not receive like this that other power consumption equipments disturb on the aircraft, functional reliability is high.
In the pattern of traditional permagnetic synchronous motor output three phase mains, have only the output of one road three-phase, when the armature winding failed because of this motor, can cause the power consumption equipment can't operate as normal.If use two motors to backup each other, can increase the volume weight of motor, mounting means is complicated.This patent adopted same many to pole permanent magnet motor on; Position and connected mode through the reasonable Arrangement stator winding; Realize the function of a motor, the output of two-way three-phase, and the armature winding of this two-way three-phase output is almost independent on magnetic circuit, it is less to interact; When one road armature winding failed because wherein, armature winding can operate as normal in addition.Realized reliable fault tolerance, and simple in structure, and cost is lower.
Have rectifier bridge in traditional power-supply system, the efficient of complete machine can not fundamentally improve, the occasion especially low, that output current is big in engine speed, and the loss of rectifier bridge is particularly serious.With switching tube replacement rectifier bridge underarm diode, can improve motor load power factor (PF) and system effectiveness, and circuit structure is simple, driving is convenient.
Summary of the invention
The scheme of the magneto alternator that novel high reliability aircraft special power-supply system employing aircraft engine directly drives and the converting means of wide range input voltage.The range of speeds that system configuration is simple, efficient is high, reliability is high and suitable is wide.The scheme that the two phase permanent magnet synchronous generator that this system adopts aircraft engine directly to drive combines with the converting means of wide range input voltage.
At first, the present invention innovates on the basis of traditional many motors fault tolerable circuit, realizes same two pairs of utmost point motor two-way output three phase mains, and magnetic circuit is almost independent between two-way voltage output simultaneously, realizes very strong fault tolerance.Be primarily characterized in that: in two pairs of pole permanent-magnet synchronous machines, stator winding through be linked in sequence, go here and there around mode, output two-way three-phase voltage.
Secondly, on traditional rectifier circuit basis, innovate, the two-way three phase mains is input to three-phase half control rectification circuit respectively; Through the closed-loop control switching tube, make circuit working in different buck patterns, finally obtain burning voltage; Be primarily characterized in that: this circuit is made up of prime three-phase half control rectification circuit and back level BUCK circuit; Pipe conducting when output voltage is low down in the front stage circuits, and the self-induction of utilizing armature winding is operated in BOOST (boosting) circuit state as inductance.High pressure output pipe is at present turn-offed, diode antiparallel (or body diode of MOSFET) conducting with it, and front stage circuits is operated in the three phase full bridge rectification state.At last by back level BUCK (step-down) converter step-down, regulated output voltage.
The scheme of this magneto alternator that this patent is taked and the converting means of wide range input voltage has following advantages:
(1) on same two pairs of pole permanent-magnet synchronous machines, realize the independently three-phase output of two-way magnetic circuit, wherein during one tunnel fault, other one the tunnel all can normally move, and very strong fault-tolerant ability is arranged, and simple in structure, power density is big.
(2) scope of the input voltage of circuit can be very wide, when motor speed changes greatly, influence output voltage values and change than greatly the time, through closed-loop control, still can stablize output dc voltage, and is reliable.
(3) circuit adopts the form of half control, and when input voltage was low, armature winding can serve as the inductance in the BOOST circuit, need not other independently inductance, thereby has reduced the volume and weight of system.
Description of drawings
Two pairs of utmost point two-way three-phase output magneto alternators are carried out the explanation of patent herein.
Fig. 1 is the structure chart of two pairs of utmost point two-way three-phase output magneto alternators
Fig. 2 is a three-phase half control rectification circuit sketch map
Fig. 3 is the control circuit sketch map of three-phase half control rectification circuit
Fig. 4 is a BUCK circuit control circuit diagram
One road three-phase output voltage and armature winding current waveform when Fig. 5 is operate as normal
Other one road three-phase output voltage and armature winding current waveform when Fig. 6 is one tunnel one phase short circuit
Other one road three-phase output voltage and the winding current waveform of counting when Fig. 7 is one road three-phase shortcircuit
The main designation of Fig. 1---Fig. 4: (1) v
In1, v '
In1---input ac voltage; V
In2, V '
In2---input direct voltage; V
O1, V
O2, V '
O1, V '
O2---output dc voltage.(2) C, C '---prime output filter capacitor; C
o, C '
o---back level output filter capacitor.(3) S
1～S
3, S '
1～S '
3, S, S '---power switch pipe.(4) D
1～D
3, D '
1～D '
3---rectifier diode; D
4～D
6, D '
4～D '
6, D, D '---fly-wheel diode.(5) L---inductance.
Embodiment
The motor topology of this patent is as shown in Figure 1; Rotor is that two pairs of permanent magnetism are staggeredly placed; Being armature winding on the stator, stator circumference is divided into uniform two sections (two half cycles), is 6 grooves on every section; Three phase windings all through string around form and equal intervals be that the winding of 2 grooves is connected, last three grooves by adjacent 1 groove in all intervals are drawn A, B, C three-phase voltage line end.Permanent magnet is two pairs of utmost points, and stator promptly moves one-period with respect to rotor rotation half cycle 180 degree mechanical angles on magnetic field, and 60 degree at interval on the A, B, C three-phase physical location, so output phase differs the three-phase voltage of 120 degree.Another corresponding half cycle is exported other one group of three-phase voltage.
The main circuit topology of this patent is as shown in Figure 2.Be divided into two-stage on the main body, prime is a three-phase half control rectification circuit, output voltage V
O1, through filter capacitor, being input to the back level, the back level is the BUCK circuit.
Wherein, the three phase electric machine winding is arranged, power switch pipe, rectifier diode, fly-wheel diode, output filter capacitor on the prime three-phase half control rectification circuit.Its connected mode is: switch S
1/ S
2/ S
3Drain electrode respectively with input three-phase alternating-current supply U
In1Three-phase A/B/C exit link to each other, grid is input as the closed-loop control signal.Three source electrodes link to each other and link to each other with the negative input end of the BUCK circuit of back level.Rectification diode D
1/ D
2/ D
3Anode respectively with S
1/ S
2/ S
3Drain electrode link to each other, negative electrode connects together and links to each other with the positive input terminal of back level BUCK circuit.Sustained diode
4/ D
5/ D
6Anode respectively with S
1/ S
2/ S
3Grid link to each other, negative electrode respectively with S
1/ S
2/ S
3Drain electrode link to each other.The two ends of prime output filter capacitor C link to each other with negative terminal with the anode of back level BUCK circuit respectively.
Back level BUCK circuit has power switch pipe, fly-wheel diode, inductance, filter capacitor.Its connected mode is: the drain electrode of switching tube S connects the anode of prime output, and grid links to each other with the negative electrode of sustained diode.The anode of sustained diode links to each other with the negative terminal of prime output.Inductance L is connected the negative electrode and the output filter capacitor C of sustained diode
oAnode between, the negative terminal of filter capacitor links to each other with the negative terminal of output.
Fig. 3 is the control circuit flow chart of three-phase half control rectification circuit, to the prime output voltage U
O1Voltage sample is with reference voltage U
Ref1Relatively, carry out error through error amplifier and amplify, compare through comparator with existing triangular carrier, be output as PWM square-wave frequency modulation ripple, this modulation wave signal is input to control logic generative circuit input, the output pulse wave signal comes control switch pipe S
1/ S
2/ S
3Switch, to stablize its prime output end voltage as far as possible.Concrete control logic is: when detecting the prime output voltage U
O1When too high, through closed-loop control power tube S
1/ S
2/ S
3Be shutoff, simultaneously D
4/ D
5/ D
6Afterflow, prime operate in the three-phase bridge rectification circuit operating state; When detecting the prime output voltage U
O1Cross when hanging down, through closed-loop control power tube S
1/ S
2/ S
3Be open-minded, this moment D
4/ D
5/ D
6Be oppositely not conducting, motor windings is all served as the inductance in the BOOST circuit, and prime operates in BOOST booster circuit operating state; Between motor speed was than lowstand, the output three-phase voltage was lower, thereby can make the prime output voltage U
O1Cross low, when reaching a certain value range, through the closed-loop control power tube, make prime stable be operated in the BOOST circuit-mode, boost to U
O1Be the 38V VD; During motor speed was higher, the output three-phase voltage was higher, thereby can make the prime output voltage U
O1Too high easily, through the closed-loop control power tube, make prime most of the time steady operation in the full-bridge rectification pattern, output voltage is used for the input of back level.
Fig. 4 is a back level BUCK circuit control circuit flow chart, to back level output voltage U
O2Voltage sample is with reference voltage U
Ref2Carry out error through comparison amplifier and amplify, output valve and inductive current sampled value * i be through voltage comparator generation PWM square-wave frequency modulation ripple, and this modulation wave signal i.e. direct turning on and off of power controlling pipe S.Take two closed-loop controls of output voltage closed loop and electric current loop in this control, realized output galvanic current pressure more easily.
Through ANSOFT software the magneto alternator of two pairs of utmost point two-way output has been carried out the fault simulation contrast under the constant situation of band resistive load.The output of one road three-phase voltage and current waveform when Fig. 5 is operate as normal are P through calculating this road power output
Onorma=110.21KW; Other one tunnel three-phase output voltage and current waveform when Fig. 6 is one tunnel one phase armature winding short circuit, this road power output that calculates through effective value is P
Alshort=106.57KW; Other one tunnel three-phase output voltage and current waveform were P through calculating this road power output when Fig. 7 was the equal short circuit of No. one threephase armature winding
O3short=108.99KW.Can find out that on oscillogram when wherein riches all the way when giving birth to short trouble, the voltage waveform of other one tunnel output is almost constant, and power output is constant basically.
Claims (2)
1. the present invention relates to a kind of aircraft engine special power-supply system, the range of speeds that system configuration is simple, efficient is high, reliability is high and suitable is wide.The scheme that the three-phase permanent synchronous generator that this system adopts aircraft engine directly to drive combines with the converting means of wide range input voltage.This system selects the magneto alternator of two pairs of utmost points, the output of two-way three-phase for use; The two-way three phase mains is exported by same motor, but independent on magnetic circuit, when one road armature winding short circuit wherein; Other one road winding still can normally be exported, and possesses very strong fault-tolerant ability.
2. the two-way three-phase voltage is input to three-phase half control rectification circuit respectively; Switching tube conducting when input line voltage is low down in this circuit, the self-induction of utilizing armature winding is served as BOOST (boosting) circuit inductance as inductance; Need not independently inductance, thereby reduce the volume and weight of system.High pressure is exported switching tube shutoff at present, diode antiparallel (or body diode of MOSFET) conducting with it, and level realized the stable of output voltage by BUCK (step-down) converter again after circuit played the three phase full bridge rectified action.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101314257A CN102664577A (en) | 2012-05-02 | 2012-05-02 | High-power-factor and high-reliability power supply dedicated for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012101314257A CN102664577A (en) | 2012-05-02 | 2012-05-02 | High-power-factor and high-reliability power supply dedicated for aeroengine |
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| Publication Number | Publication Date |
|---|---|
| CN102664577A true CN102664577A (en) | 2012-09-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101314257A Pending CN102664577A (en) | 2012-05-02 | 2012-05-02 | High-power-factor and high-reliability power supply dedicated for aeroengine |
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| CN (1) | CN102664577A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI465030B (en) * | 2012-10-30 | 2014-12-11 | Ind Tech Res Inst | Multi-driving device and driving circuit thereof |
| CN104506113A (en) * | 2014-12-31 | 2015-04-08 | 南京航空航天大学 | Control method for drive system of duplex-winding permanent magnet fault tolerant motor |
| CN104836496A (en) * | 2015-05-25 | 2015-08-12 | 江苏苏美达机电科技有限公司 | DC generator set |
| CN107147225A (en) * | 2017-07-02 | 2017-09-08 | 天津飞眼无人机科技有限公司 | The magnetic motive force drive and its control system of rotor wing unmanned aerial vehicle |
| CN108945485A (en) * | 2017-05-17 | 2018-12-07 | 通用电气公司 | Propulsion system for aircraft |
| CN112104241A (en) * | 2020-09-16 | 2020-12-18 | 隆鑫通用动力股份有限公司 | Engine generator |
| CN113746191A (en) * | 2021-09-24 | 2021-12-03 | 中国北方车辆研究所 | Method for constructing direct current +/-28V power supply by adopting permanent magnet motor |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5929549A (en) * | 1998-04-02 | 1999-07-27 | Pacific Scientific Company | Fault tolerant electric machine |
| CN101325357A (en) * | 2007-06-15 | 2008-12-17 | 陈国弟 | Automobile permanent magnet generator with tiny output voltage ripple |
| CN101951099A (en) * | 2010-08-25 | 2011-01-19 | 哈尔滨工业大学 | High-performance direct-current (DC) output permanent magnet generator system |
| CN102223085A (en) * | 2011-06-17 | 2011-10-19 | 南京航空航天大学 | Power system special for aircraft engine formed by combining hybrid excitation generator and direct-current (DC) converter |
| CN102227095A (en) * | 2011-06-17 | 2011-10-26 | 南京航空航天大学 | High efficiency power supply system specially used by aeroengine |
-
2012
- 2012-05-02 CN CN2012101314257A patent/CN102664577A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5929549A (en) * | 1998-04-02 | 1999-07-27 | Pacific Scientific Company | Fault tolerant electric machine |
| CN101325357A (en) * | 2007-06-15 | 2008-12-17 | 陈国弟 | Automobile permanent magnet generator with tiny output voltage ripple |
| CN101951099A (en) * | 2010-08-25 | 2011-01-19 | 哈尔滨工业大学 | High-performance direct-current (DC) output permanent magnet generator system |
| CN102223085A (en) * | 2011-06-17 | 2011-10-19 | 南京航空航天大学 | Power system special for aircraft engine formed by combining hybrid excitation generator and direct-current (DC) converter |
| CN102227095A (en) * | 2011-06-17 | 2011-10-26 | 南京航空航天大学 | High efficiency power supply system specially used by aeroengine |
Non-Patent Citations (1)
| Title |
|---|
| 王真等: "车用高可靠性永磁同步电动机设计及控制", 《微特电机》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI465030B (en) * | 2012-10-30 | 2014-12-11 | Ind Tech Res Inst | Multi-driving device and driving circuit thereof |
| US9065372B2 (en) | 2012-10-30 | 2015-06-23 | Industrial Technology Research Institute | Multi-driving device and driving circuit thereof |
| CN104506113A (en) * | 2014-12-31 | 2015-04-08 | 南京航空航天大学 | Control method for drive system of duplex-winding permanent magnet fault tolerant motor |
| CN104506113B (en) * | 2014-12-31 | 2017-02-22 | 南京航空航天大学 | Control method for drive system of duplex-winding permanent magnet fault tolerant motor |
| CN104836496A (en) * | 2015-05-25 | 2015-08-12 | 江苏苏美达机电科技有限公司 | DC generator set |
| CN108945485A (en) * | 2017-05-17 | 2018-12-07 | 通用电气公司 | Propulsion system for aircraft |
| CN107147225A (en) * | 2017-07-02 | 2017-09-08 | 天津飞眼无人机科技有限公司 | The magnetic motive force drive and its control system of rotor wing unmanned aerial vehicle |
| CN107147225B (en) * | 2017-07-02 | 2023-06-27 | 天津飞眼无人机科技有限公司 | Magnetomotive driver of rotor unmanned aerial vehicle and control system thereof |
| CN112104241A (en) * | 2020-09-16 | 2020-12-18 | 隆鑫通用动力股份有限公司 | Engine generator |
| CN112104241B (en) * | 2020-09-16 | 2022-07-12 | 隆鑫通用动力股份有限公司 | Engine generator |
| CN113746191A (en) * | 2021-09-24 | 2021-12-03 | 中国北方车辆研究所 | Method for constructing direct current +/-28V power supply by adopting permanent magnet motor |
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Application publication date: 20120912 |