Gas turbine engine and electrical system

• US 9,601,970 B2
• Filed: 12/19/2013
• Issued: 03/21/2017
• Est. Priority Date: 03/13/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce North American Technologies, Inc. (Rolls-Royce Holdings Plc)
• Inventors: French, Mat, Alt, John T., Blackwelder, Mark J.
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): WALTHOUR, SCOTT J
• Application Number:
  US14/135,567
• Publication Number:
  US 20140360205A1
• Time in Patent Office: 1,188 Days
• US Class Current: 1/1
• CPC Class Codes: B81B 2201/0257 Microphones or microspeakers
• CPC Class Codes: B81B 2201/0264 Pressure sensors
• CPC Class Codes: B81B 7/02 containing distinct electrical or optical devices of particular relevance for their function, e.g. microelectro-mechanical systems [MEMS] B81B7/04 takes precedence
• CPC Class Codes: B81C 1/00158 Diaphragms, membranes manufacture process for semi-permeable inorganic membranes B01D67/0039
• CPC Class Codes: B81C 1/00301 Connecting electric signal lines from the MEMS device with external electrical signal lines, e.g. through vias
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F02C 7/268 Starting drives for the rotor , acting directly on the rotor of the gas turbine to be started
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02N 11/0862 characterised by the electrical power supply means, e.g. battery
• CPC Class Codes: F05B 2220/706 an electrical generator
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2270/62 Electrical actuators
• CPC Class Codes: H02J 1/102 being switching converters H02J1/108, H02J1/12 take precedence
• CPC Class Codes: H02J 1/16 using dynamo-electric machines coupled to flywheels
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 3/30 using dynamo-electric machines coupled to flywheels
• CPC Class Codes: H02J 3/32 using batteries with converting means
• CPC Class Codes: H02J 3/38 : Arrangements for parallely feeding a single network by two or more generators, converters or transformers
• CPC Class Codes: H02J 9/061 : for DC powered loads
• CPC Class Codes: H02K 7/1823 : structurally associated with turbines or similar engines
• CPC Class Codes: H02P 2101/25 : for combustion engines
• CPC Class Codes: H02P 2101/30 : for aircraft
• CPC Class Codes: H02P 9/48 : Arrangements for obtaining a constant output value at varying speed of the generator, e.g. on vehicle H02P9/04 - H02P9/46 take precedence

Abstract

A gas turbine engine includes an electrical system that includes a controller coupled to a first inverter/converter controller, a second inverter/converter controller, and a converter/controller that is coupled to an energy storage device. The system is configured to provide electrical power to a first electrical bus and a second electrical bus, from first and second electrical machines, under the direction of the controller. The converter controller is configured to control the amount of electrical power supplied to the first electrical bus and the second electrical bus from the energy storage system. The amount of electrical power received from the first electrical bus and the second electrical bus, and energy supplied to the energy storage system are under the direction of the controller.

Claims

1. A turbomachine, comprising:

a high pressure rotor;

a low pressure rotor; and

an electrical system configured to supply power to two electrical busses, the electrical system including;

a first controller configured to control operation of the turbomachine;

a second controller coupled to the first controller;

a first electrical machine in mechanical communication with the high pressure rotor;

a second electrical machine in mechanical communication with the low pressure rotor;

a first inverter-converter controller and a third inverter-converter controller, each coupled to both the second controller and the first electrical machine, wherein the first inverter-converter controller is coupled to, and is dedicated to, a first electrical bus of the two electrical busses and is configured to provide electrical power to the first electrical bus under direction from the second controller, and wherein the third inverter-converter controller is coupled to, and is dedicated to, a second electrical bus of the two electrical busses and is configured to provide electrical power to the second electrical bus under direction from the second controller;

a second inverter-converter controller and a fourth inverter-converter controller, each coupled to both the second controller and the second electrical machine, wherein the second inverter-converter controller is coupled to, and is dedicated to, the first electrical bus and is configured to provide electrical power to the first electrical bus under direction from the second controller, and wherein the fourth inverter-converter controller is coupled to, and is dedicated to, the second electrical bus and is configured to provide electrical power to the second electrical bus under direction from the second controller;

an energy storage system configured to supply power to and absorb power from the two electrical busses; and

a converter controller coupled to the energy storage system, the second controller and the two electrical busses, wherein the converter controller is configured to control an amount of electrical power supplied to the two electrical busses from the energy storage system under direction from the second controller, and configured to control an amount of electrical power received from the two electrical busses and supplied to the energy storage system under direction from the second controller;

wherein the first inverter-converter controller and the second inverter-converter controller are configured to provide electrical power to the first electrical bus in parallel under the direction of the second controller; and

wherein the third inverter-converter controller and the fourth inverter-converter controller are configured to provide electrical power to the second electrical bus in parallel under the direction of the second controller.

2. The turbomachine of claim 1, wherein the first electrical machine is a starter/generator.

3. The turbomachine of claim 1, wherein the energy storage system is configured to absorb transient loads on the two electrical busses.

4. The turbomachine of claim 1, wherein the second controller, the first electrical machine, the second electrical machine, the first inverter-converter controller, the second inverter-converter controller, the third inverter-converter controller, and the fourth inverter-converter controller are configured for variable power sharing.

5. The turbomachine of claim 1, wherein the electrical system is configured to regulate respective voltages of the two electrical busses.

6. The turbomachine of claim 1, wherein the electrical system is configured to transfer power between the high pressure rotor and the low pressure rotor.

7. The turbomachine of claim 1, wherein the energy storage system is configured to supply power to the two electrical busses during high output operations of the turbomachine.

8. A gas turbine engine, comprising:

a high pressure spool;

a low pressure spool;

a controller; and

a first electrical machine coupled to the low pressure spool and coupled to a first inverter-converter controller and a third inverter-converter controller, with the first inverter-converter controller being coupled to, and dedicated to, a first electrical bus and the third inverter-converter controller being coupled to, and dedicated to, a second electrical bus;

a second electrical machine coupled to the high pressure spool and coupled to a second inverter-converter controller and a fourth inverter-converter controller, with the second inverter-converter controller being coupled to, and dedicated to, the first electrical bus and the fourth inverter-converter controller being coupled to, and dedicated to, the second electrical bus;

an energy storage system configured to supply power to and absorb power from the first electrical bus and the second electrical bus; and

a converter controller coupled to the energy storage system, the controller, the first electrical bus, and the second electrical bus, wherein the converter controller is configured to control an amount of electrical power supplied to the first electrical bus and the second electrical bus from the energy storage system under direction from the controller, and to control an amount of electrical power received from the first electrical bus and from the second electrical bus and supplied to the energy storage system under direction from the controller;

wherein the first inverter-converter controller and the third inverter-converter controller are configured to provide electrical power in parallel to the first electrical bus under direction from the controller; and

wherein the second inverter-converter controller and the fourth inverter-converter controller are configured to provide electrical power in parallel to the second electrical bus under direction from the controller.

9. The gas turbine engine of claim 8, wherein the first electrical machine, the second electrical machine and the energy storage system are configured to supply power simultaneously to the first and second electrical buses;

wherein the energy storage system is configured to absorb transient loads from the first and second electrical buses; and

wherein the energy storage system is configured to be charged by the first and second electrical buses.

10. The gas turbine engine of claim 8, wherein each of the first and second electrical machines is a starter/generator.

11. The gas turbine engine of claim 8, wherein the energy storage system is configured to absorb transient loads on the first electrical bus and/or the second electrical bus.

12. The gas turbine engine of claim 8, wherein the controller, the first electrical machine, the second electrical machine, the first inverter-converter controller, the second inverter-converter controller, the third inverter-converter controller, and the fourth inverter-converter controller are configured for variable power sharing.

13. The gas turbine engine of claim 8, wherein the energy storage system is configured to supply power to the first electrical bus and the second electrical bus during high thrust operations of the gas turbine engine.

14. A gas turbine engine, comprising:

a high pressure spool;

a low pressure spool; and

an electrical system configured to supply power in parallel to a first electrical bus and a second electrical bus, the electrical system including;

a first controller configured to control operation of the gas turbine engine;

a second controller coupled to the first controller;

a first electrical machine in mechanical communication with the high pressure spool;

a second electrical machine in mechanical communication with the low pressure spool;

a first inverter-converter controller and a third inverter-converter controller, each coupled to both the second controller and the first electrical machine, wherein the first inverter-converter controller is coupled to, and is dedicated to, the first electrical bus and is configured to provide electrical power to the first electrical bus under direction from the second controller, and wherein the third inverter-converter controller is coupled to, and is dedicated to, the second electrical bus and is configured to provide electrical power to the first second electrical bus under direction from the second controller;

a second inverter-converter controller and a fourth inverter-converter controller, each coupled to both the second controller and the second electrical machine, wherein the second inverter-converter controller is coupled to, and is dedicated to, the first electrical bus and is configured to provide electrical power to the first electrical bus under direction from the second controller, and wherein the fourth inverter-converter controller is coupled to, and is dedicated to, the second electrical bus and is configured to provide electrical power to the second electrical bus under direction from the second controller;

an energy storage system configured to supply power to and absorb power from the first electrical bus and the second electrical bus; and

a converter controller coupled to the energy storage system, the second controller, the first electrical bus, and the second electrical bus, wherein the converter controller is configured to control an amount of electrical power supplied to both the first electrical bus and the second electrical bus from the energy storage system under direction from the second controller, and to control an amount of electrical power received from both the first electrical bus and the second electrical bus and supplied to the energy storage system under direction from the second controller.

15. The gas turbine engine of claim 14, wherein the first electrical machine is a starter/generator.

16. The gas turbine engine of claim 14, wherein the energy storage system is configured to absorb transient loads on the first electrical bus and/or the second electrical bus.

17. The gas turbine engine of claim 14, wherein the second controller, the first electrical machine, the second electrical machine, the first inverter-converter controller, the second inverter-converter controller, the third inverter-converter controller, and the fourth inverter-converter controller are configured for variable power sharing.

18. The gas turbine engine of claim 14, wherein the electrical system is configured to regulate a voltage of the first electrical bus and/or a voltage of the second electrical bus.

19. The gas turbine engine of claim 14, wherein the electrical system is configured to transfer power between the high pressure spool and the low pressure spool.

20. The gas turbine engine of claim 14, wherein the energy storage system is configured to supply power to the first electrical bus and the second electrical bus during high thrust operations of the gas turbine engine.