Power supply system with first and second AC voltage generators and respective 6-pulse rectifier units

Abstract

A power supply has first and second ac voltage generators. Both of the first and second ac voltage generators are connected to one or more loads and a respective 6-pulse rectifier unit for rectifying ac voltage from each of the first and second power generators to a dc voltage output for the loads, Both of the first and second ac voltage generators includes two 3-phase voltage sources separated by a phase shift. The voltage output from each rectifier unit is coupled to the loads via a respective interphase inductor.

Claims

1. A power supply comprising: first and second ac voltage generators, wherein both the first and second ac voltage generators are connected to one or more loads and wherein the first and second ac voltage generators are connected to respective first and second 6-pulse rectifier units for rectifying ac voltage from each of the first and second ac voltage generators to a dc voltage output for the loads, wherein each of the first and second ac voltage generators comprises two 3-phase voltage sources separated by a phase shift, wherein the voltage output from each rectifier unit is coupled to the loads via a respective interphase inductor; and a third ac voltage generator connected to the one or more loads and having a further two 3-phase voltage sources separated by a phase shift and further comprising a respective further rectifier unit for each of the further two 3-phase voltage sources; wherein: a first rectifier unit receives inputs from a first 3-phase source (a,c) of each of the first and second ac voltage generators and a second rectifier unit receives inputs from a second 3-phase source (b,d) of each ac voltage generator; wherein the first rectifier unit provides a first dc output (e) and the second rectifier unit provides a second dc output (f); wherein the first dc output (e) is connected to the loads and to the second rectifier unit via a first interphase inductor, and the second dc output (f) is connected to the loads and to the first rectifier unit via a second interphase inductor; and wherein the two sources for the third ac voltage generator are connected into the output via two further rectifier units, which are also connected in parallel via respective interphase inductors to output the loads; wherein the power supply is in combination with a geared turbofan engine, wherein the second ac voltage generator is associated with a high spool side of the engine and the third ac voltage generator is associated with a low spool side of the generator.

2. The power supply of claim 1, wherein the phase shift is 30 degrees.

3. The power supply of claim 1, wherein a first rectifier unit receives inputs from a first 3-phase source (a,c) of each ac voltage generator and a second rectifier unit receives inputs from a second 3-phase source (b,d) of each ac voltage generator, and wherein the first rectifier unit provides a first dc output and the second rectifier unit provides a second dc output (f), wherein the first dc output (e) is connected to the loads and to the second rectifier unit via a first interphase inductor, and the second dc output (f) is connected to the loads and to the first rectifier unit via a second interphase inductor.

4. The power supply of claim 1, further comprising a control unit arranged to regulate power supply to the loads.

5. An aircraft power supply, comprising the power supply of claim 1, wherein the first ac voltage generator is an external ground generator and the second ac voltage generator is an on-board generator.

6. The aircraft power supply of claim 5, wherein the external ground generator powers the loads when the aircraft is on the ground, and the on-board generator powers the loads when the aircraft is in flight.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a schematic view of a conventional HVDC power supply system.

(2) FIG. 2 is a schematic view of an HVDC power supply system according to this disclosure.

(3) FIG. 3 is a variation of the system shown in FIG. 2 for a GTF engine.

(4) FIG. 4 is a variation of the system of FIG. 2 for an electric start motor.

DETAILED DESCRIPTION

(5) Referring to FIG. 1, the conventional systems mentioned above will be briefly described.

(6) When the aircraft is on the ground, power is supplied to the loads 10 e.g. on-board systems from an external AC generator 1 via a rectifiereither an ATRU 2 or an active rectifier 3 that provides DC voltage 4 for the loads 10. During flight, the aircraft systems are powered from the aircraft engine or APU 5 via a variable frequency generator 6. The AC voltage is rectified by a rectifier unit 7 to provide the DC voltage 4 for the loads 10. A general control unit GCU regulates the power supply at the point of regulation POR at the dc end of the system. The HVDC bus is required to have a parallel-connected large bus capacitor to ensure voltage stability and to reduce voltage ripple to an acceptable level. This leads to a poor dynamic response of voltage regulation on fast load variation. The presence of a large capacitor can also affect the reliability of the whole power channel.

(7) To overcome the problems of the prior art systems, the systems according to the present invention use dual 3-phase generators with a phase shift of preferably 30 deg, for each generator and interphase inductors to mutualise the rectifier units associated with the respective power sources as will be described further below with reference to FIGS. 2 to 4.

(8) As with conventional systems, the aircraft is powered, when on the ground, by an external generator 1, via a transformer unit 11 and when in flight, by the aircraft engine or APU 5 via a VFG 6. Each of these generators comprises two 3-phase voltage sources a,b,c,d separated by a 30 deg. phase shift. Each generator is associated with a respective 6-pulse rectifier RU 8,9.

(9) To save weight, the two rectifier units 8,9 are mutualised between the transformer unit 11 and the engine/APU 5. In more detail, the first rectifier unit 8 receives inputs from the first 3-phase source a,c of each generator and the second unit 9 receives inputs from the second 3-phase source b,d of each generator. The first rectifier unit 8 provides a first dc output e and the second rectifier unit 9 provides a second dc output f. The first dc output e is connected to the loads 10 and to the second rectifier unit 9 via a first interphase inductor 12. The second dc output f is connected to the loads 10 and to the first rectifier unit 8 via a second interphase inductor 13. Thus, the two sets of rectified voltages are coupled in parallel through the interphase inductors which minimises the voltage ripple on the dc bus without capacitors. The use of two parallel rectifier units also provides redundancy for the event of failure of one of the units. A control unit 14 regulates the power supply at the point of regulation POR at the dc end of the system.

(10) The 12-pulse rectification technique caused by the dual 3-phase sources and the two 6-pulse rectifiers produces very low ripple without the need for a capacitor. Also, the point of failure that is the capacitor is avoided by use of the interphase inductors.

(11) When the external power generator is disconnected, a 3-phase 115 V ac voltage can still be produced and be available for conventional loads by coupling the transformer unit 11 secondary windings to the VFG stators (separated by 30 deg). Thus, a 115V ac bus is powered from the external generator when operating on the ground, with the engine/APU stopped. This can be used for ground services on the aircraft. If the transformer unit 11 has its primary windings connected in a Wye configuration, access to ground and a single load supply is possible.

(12) During flight, when the aircraft engine/APU are running and powering the loads, this 115 V ac bus can still be supplied without external power, through the transformer unit 11 operating in a reversed manner. In more detail, the TU secondary windings are powered from the VFG 6. The transformer unit 11 converts its 230 V ac voltage back to 115 V ac. [The transformer unit (TU) having one primary winding and two secondary windings with a 30 phase shift (Wye Delta) between them is reversible 1) When the A/C is supplied from the external power, the 115 Vac bus is directly supplied from external power that supplies the TU primary winding and the 115 Vac bus connected in parallel. In this case the two TU secondary windings produce 2230 Vac sets with a 30 phase shift. These two voltages are rectified by RUs and combined with interphase inductors to produce the HVDC bus. 2) When the A/C is supplied by the engine generators, the two VFG sets of 230 Vac voltage supply the RUs with a 30 phase shift and are combined with interphase inductors to produce HVDC. At the same time, the two 230 Vac outputs of a VFG supply respectively the two TU secondaries with a phase shift of 30. The TU works in opposite direction (power flow is reversed) stepping down the 230 VAC voltages into a 3 phase AC 115V to supply the A/C AC bus.

(13) FIG. 3 shows a variation on the system described above, for use with a geared turbofan (GTF) engine. A GTF engine has a high spool and a low spool and it is considered desirable to provide two three-phase sources for each of the high and the low spool, each separated by a phase shift e.g. 30 deg. The system is comparable to the system of FIG. 2 for the low spool side of the engine and the external generator. In addition, though, the two sources for the high spool are connected into the output via two more rectifier units 15,16. These are also connected in parallel via respective interphase inductors 17,18 to operate in a manner similar to above, the outputs connected to the loads at the POR.

(14) A further modification of the concept, adapted for electric starter engines (of all types) is shown in FIG. 4. Here, instead of a VFG associated with the aircraft engine two signals from two signal generators 20,21, with phase shifts of 30 deg. are output to the loads. Instead of rectification units, 3-phase power reversible inverters, or power electronic modules (PEMs) 30,31,32,33 are used. A PEM can be a single module or several modules connected in parallel, thus sharing power flow in one or the other direction. The PEM outputs are provided to the loads via interphase inductors in a manner similar to that for the embodiment of FIG. 3 The overall system is managed by two redundant starter generator and ground power control units (SGGPCUs) 40,50.

(15) When operating in generation mode, the gates of the switches of the PEMs can all be off. The PEMs operate in passive rectification mode. When starting the engine, the PEMs are supplied from the HVDC bus

(16) In addition to the 30 phase shift of the stators, the starter generator's input shaft can be keyed on the engine gearbox outputs so that there a mechanical angle shift between them and rotors leading to an electrical angle phase shift of the voltages generated of 15 by the first (or second) stator of the first generator and by the first (or, respectively, second) stator of the second generator. In generation mode, this brings further improved power quality/reduced voltage ripple on the HVDC bus (equivalent to 24-pulse rectification) when both machines are paralleled on the same bus. In engine start mode, this brings reduced torque ripple.

(17) Further, the fact that the starter/generator are dual-star stators enables a built-in rotor position sensor and thus the so-called resolver deletion (cost, weight saving and improved reliability). Indeed, before the engine start sequence, we can stimulate one stator by a 3-phase e.m.f and measure the voltages generated on the other 3-phase stator, the ratio between stimuli magnitude and measured magnitude is a function of rotor position for a salient pole machine (variable reluctance).

(18) The concepts described herein provide power supply systems that avoid the need for and problems associated with capacitors, as well as providing very low ripple and providing a smaller and lighter system with redundancy features for added safety. There is also no need for a heavy neutral cable from the ac source that is required in existing systems. The dc voltage can be smoothly and quickly regulated at the dc end of the supply.