Dual output synchronous-induction starting/generating system

• US 5,587,647 A
• Filed: 06/30/1995
• Issued: 12/24/1996
• Est. Priority Date: 06/30/1995
• Status: Expired due to Fees

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Bansal, Madan L., Vaidya, Jayant G.
• Primary Examiner(s): Stephan, Steven L.
• Assistant Examiner(s): Ponomarenko, Nicholas
• Application Number:
  US08/497,036
• Time in Patent Office: 543 Days
• Field of Search: 322/45, 322/47, 322/32, 290/6, 290/31
• US Class Current: 322/45
• CPC Class Codes: F02N 11/04 the motors being associated with current generators
• CPC Class Codes: H02K 17/42 Asynchronous induction generators H02K17/02 takes precedence
• CPC Class Codes: H02K 19/28 for self-excitation

Abstract

An electric power starter generator system comprises a synchronous generator and an induction motor/generator mutually coupled to a shaft being driven to an external prime mover. The synchronous generator and the induction motor/generator are driven by the shaft at the same speed. The system includes a rectifier/inverter having ac terminals coupled to the output of the induction motor/generator, and dc terminals coupled to a dc bus. This rectifier/inverter allows bi-directional power flow to effectuate both power generation as well as electric start of the prime mover. The synchronous generator is excited by a commonly driven permanent magnet generator and a modulated exciter field control. The induction motor/generator is self-exciting through the rectifier/inverter once a voltage is established on the dc bus. The establishment of this voltage may be accomplished by a battery, or by connection of the synchronous generator'"'"'s output to the input of the rectifier/inverter through a poly-phase contactor. This contactor also allows cross connection of either machine to either distribution bus if one of the machines were to fail, or if the loading on that particular bus became excessive.

Claims

1. An electric power starter generator system, comprising:

a synchronous generator having a first rotor and a first polyphase stator output coupled to an ac bus;

an induction motor/generator having a second rotor and a second polyphase stator output;

a shaft coupled to said first rotor of said synchronous generator and to said second rotor of said induction motor/generator, said shaft being drivably coupled to an external prime mover, said shaft driving said synchronous generator and said induction motor/generator at a same speed thereby; and

a rectifier/inverter having ac terminals coupled to said second polyphase stator output and dc terminals coupled to a dc bus, said rectifier/inverter allowing bi-directional power flow therethrough.

2. The system of claim 1, further comprising first means for exciting said synchronous generator when said shaft is being driven by the prime mover, said first means controlling a first ac output voltage resulting therefrom.

3. The system of claim 2, wherein said first means comprises:

a permanent magnet generator coupled to said shaft and driven thereby at said same speed as said synchronous generator and said induction motor/generator, said permanent magnet generator generating an electrical output in response to rotation of said shaft;

a rectifier electrically coupled to said permanent magnet generator, said rectifier generating a dc voltage in response to said permanent magnet generator'"'"'s electrical output;

a voltage regulator sensibly coupled to said ac output voltage of said synchronous generator, said voltage regulator modulatably coupling said dc voltage to an exciter field of said synchronous generator to control said ac output voltage generated in response thereto.

4. The system of claim 2, wherein said first ac output is additionally switchably coupled by a polyphase contactor to said ac terminals of said inverter/rectifier, said inverter/rectifier producing a dc voltage in response thereto, said dc voltage charging a capacitor coupled across said dc bus.

5. The system of claim 4, wherein once a voltage is established across said capacitor, said inverter/rectifier operates to excite said second polyphase stator of said induction motor/generator, said induction motor/generator generating a second ac output thereby.

6. The system of claim 5, wherein said polyphase contactor opens to maintain isolation between said first ac output generated by synchronous generator and a second ac output generated by said induction motor/generator, and wherein said polyphase contactor closes if either said first or said second ac outputs are not being generated.

7. The system of claim 1, wherein the prime mover drivably coupled to said shaft is an engine, and wherein said inverter/rectifier operates to generate a third ac voltage from a dc voltage from an external source on said dc bus, said third ac voltage exciting said second polyphase stator of said induction motor/generator causing rotation of said second rotor thereby to rotate said shaft to allow starting of the engine.

8. An aircraft electric power starting and generating system, comprising:

an aircraft engine;

a shaft divably coupled to said aircraft engine;

a synchronous generator having a first rotor directly coupled to said shaft, and a first polyphase wound stator coupled to an ac distribution bus;

an induction motor generator having a second rotor directly coupled to said shaft, and a second polyphase wound stator;

a bi-directional ac/dc converter having a polyphase ac input coupled to said second polyphase wound stator, and a dc output coupled to a dc distribution bus; and

wherein said bi-directional ac/dc converter draws power from the dc bus to excite said second stator to cause said second rotor to rotate said shaft to allow starting of said aircraft engine.

9. The system of claim 8, wherein said bi-directional ac/dc converter draws power from the dc bus to excite said second stator to allow said induction motor/generator to generate ac electric power during operation of said engine, said bi-directional ac/dc converter converting said generated ac electric power into dc electric power to supply the dc distribution bus, said induction motor/generator operating in a self exciting generation mode thereby.

10. The system of claim 8, further comprising a polyphase ac contactor switchably coupling said first polyphase wound stator to said second polyphase wound stator.

11. The system of claim 8, further comprising first means for exciting said synchronous generator when said shaft is being driven by said aircraft engine, said synchronous generator generating an ac output in response thereto.

12. The system of claim 11, wherein said first means comprises:

a permanent magnet generator coupled to said shaft and driven thereby, said permanent magnet generator generating an electrical output in response to rotation of said shaft;

a rectifier electrically coupled to said permanent magnet generator, said rectifier generating a dc voltage in response to said permanent magnet generator'"'"'s electrical output;

a voltage regulator sensibly coupled to said ac output voltage of said synchronous generator, said voltage regulator modulatably coupling said dc voltage to an exciter field of said synchronous generator to control said ac output voltage generated in response thereto.

13. The system of claim 11, wherein said polyphase ac contactor couples said first wound stator to said bi-directional ac/dc converter to produce dc power to charge a capacitor on said dc distribution bus, said polyphase ac contactor thereafter opening to allow said bidirectional ac/dc converter to energize said second stator, said induction motor/generator producing ac electric power thereby, said bidirectional ac/dc converter converting said ac electric power to dc power to supply said dc distribution bus, said induction motor/generator operating in a self exciting generation mode thereby.